US2559131A - Hollow blade for gas turbines and the like - Google Patents
Hollow blade for gas turbines and the like Download PDFInfo
- Publication number
- US2559131A US2559131A US86703A US8670349A US2559131A US 2559131 A US2559131 A US 2559131A US 86703 A US86703 A US 86703A US 8670349 A US8670349 A US 8670349A US 2559131 A US2559131 A US 2559131A
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- United States
- Prior art keywords
- blade
- root
- pin
- assembly
- cooling fluid
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
Definitions
- the cooling fluid is introduced either laterally through ports provided in the vicinity of the root of the blade on the leading edge and the trailing edge of the latter or again through a recess provided between the root of the blade and the blade carrier, said recess being provided in one side of theroot assuming the shape of a case, which I side extends beyond the blade carrier.
- the channels feeding the blades communicate with a chamber formed by a covering metal sheet and the blade carrier and into which is introduced the cooling fluid.
- the drawbacks of known blades of this type consist in that they hardly satisfy the conditions of mechanical resistance and of secure fixation that are necessary for turbine blades, that the root of the blade and corresponding recess in the blade carrier are of a comparatively dimcult execution, that the securing inside the blade of the diaphragm intended for instance for the guiding of the cooling medium is a difficult matter, that the blades are interchangeable with some difllculty and the introduction of the cooling fluid into the blade leads to considerable losses by reason of the marked bands of the circuit and unavoidable losses.
- the object of the invention is to provide a hollow blade that allows removing the above drawbacksand also the execution of a blade root, starting from a single blank of sheet metal. This is obtained by forming the blade in the following manner:
- the metal sheet forming the wall of the blade is bent at one end so as to form the root, the cross-section of which assumes preferably the shape of a segment of a circle.
- the connection between the root and the body of the blade is performed at the ends of said segment along both sides of the bent blade through a plane 13 Claims. (01. 60-41) surface that provides together with the root for the fitting and guiding of the blade over the turbine wheel.
- the root is reinforced by an inserted pin and shows at its lower end one or more openings intended for the axial passage of the cooling fluid from the turbine wheel.
- the hollow blade forming the object of the invention includes therefore a Laval type or similar root, that is well known per se and has proved satisfactory for solid blades.
- Fig. 1 is a lateral elevational view of a hollow blade according to the invention.
- Fig. 2 is 'a cross-section on a larger scale through line AA of Fig. 1.
- Fig. 3 is a cross-section through line BB of Fig. 2.
- Fig. 4 illustrates a modified shape that may be given to the trailing edge of the blade.
- Figs. 5, 6 and 7 illustrate respectively in elevational view, in cross-sectional view and in longi- 'tudinal section a flat blank of sheet metal used for executing the blade.
- Figs. 8 and 9 illustrate a manner of mounting the blade according to the invention on a turbine rotor.
- Fig. 8 is a partial elevational view of the rotor seen from the side corresponding to the leading edge while Fig. 9 is a crosssection through line 12-13 of Fig. 8.
- the blade shown in Figs. 1 to 3 is obtained through the folding inside dies, by means of shaped tools, of a flat blank of sheet metal as illustrated in Figs. 5, 6 and 7.
- the pin 4 is welded to the sheet metal forming the blade at both ends of said spindle and along the joining surface 6.
- the welding seam 8 provided on the side corresponding to the leading edge of the blade extends throughout the periphery of the pin 4 while the welding for the side corresponding to the trailing edge of the blade extends only over the lower half of the root for reasons of mechanical resistance.
- the welding seam closing the body I of the blade extends over the trailing edge 10 only up to a point ll (Fig. 1) From this standpoint, it should be remarked that it is also possible to weld the pin 4 to the sheet metal forming the blade I and also to weld the latter along the joint 6 and further to weld the trailing edge It] in a manner such that the blade may be hermetically sealed throughout its surface except for the opening 5 provided in the root for the introduction of the cooling fluid and also for the opening provided for the output of said cooling fluid that is preferably provided at the tip of said blade.
- the pin 4 In register with the opening 5, the pin 4 assumes a lesser cross-section so that the cooling fluid may pass into the inside of the blade to either side of the reduced pin portion 40. along the direction illustrated by the arrows.
- the crosssection of the reduced part of the pin may be given any desired shape.
- the pin may be constituted by two separate members that are fitted into the root through the opposed ends thereof.
- the blade includes as in the embodiment illustrated a diaphragm l2 that serves for guiding the cooling air or for damping the vibrations or again simultaneously for both purposes said diaphragm' 12 engages the slot I3 of the pin 4 and extends into the lower end of the root where it is welded to the pin 4.
- the root illustrated that has a transversal cross-section in the shape of a circular sector may be replaced by a-root of any desired crosssection that may be for instance square, rectanguerated through points or along a continuous line.
- the starting material used for producing the blade through a folding of a flat sheet of metal is constituted according to the invention by a blank l5 cut to the desired shape as illustrated in Figs. 5, 6 and '7.
- said blank appears substantially as a rectangular member provided at one end with four rectangular lugs, l6-l1--l8-l9 adapted to'form the root of the blade.
- the size and spacing of the lugs are defined by the size of the openings to be provided in the root and by the diameter of the latter. It is preferable to make use of a metal sheet the thickness of which gradually decreases from the root towards the tip of the blade as illustrated in Fig. 7, that is a cross-section through line D-D of Fig. 5.
- the two edges Illa and lb of the blank that are to bear against one another after folding so as to form the trailing edge ll) of the blade are bevelled on their inner side in the manner illustrated in Fig. 6, that is a cross-section through line C-C of Fig. 5.
- the depth of the bevel diminishes gradually from the root towards the tip of the blade as shown in dotted lines at 20a. and 20b in Fig. 5.
- Figs. 8 and 9 In the manner of mounting the blade according to the invention on a turbine wheel as illustrated in Figs. 8 and 9, said blade is fitted in corresponding grooves 2
- the reference number 23 designates the disc of the wheel carrying the blades while .24 designates a locking ring engaging the grooves [4 of the different blades, 25 a balancing member and 26 one of the channels provided through the rim 22 and through which the cooling fluid is fed to the blade or to the openings 5 provided in the root of the blades and progressing in the direction of the arrows.
- Fig. 8 shows in interrupted lines three such channels 26 that receive the cooling fluid from the chamber 21 formed by the disc 23, the rim 22 and the cover 28. This cooling fluid is fed to said chamber through suitable ducts that are not illustrated.
- the cooling fluid is admitted into the blade and flows through same without any sharp turns and the channelling system shows no leaking point.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body atthe root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to saidhollow body.
- An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body 3.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass
- the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, flat portions being provided between said body and the bent part of said lugs, said flat portions being parallel with one another and spaced by a distance less than the maximal width of said tubular assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
- An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a cylindrical tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, a welded seam being provided between the abutted ends of said lugs at the lower part of said root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly having an aperture therethrough and said pin including two parts separated by a gap registering with said aperture to provide a cooling fluid inlet passage to said hollow body.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; a pin provided with a diametrical slot fitted in said assembly and a metal sheet diaphragm located longitudinally inside the blade and including an extension engaging said slot in said pin and welded to said pin, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
- an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a polygonal tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
- An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length; two pairs of spaced lugs projecting from said hollow body at the root end of the front and rear part thereof respectively, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly 7 provided with a central aperture therethrouth; UNITED STATES PATENTS and a pin fitted in said assembly, said pin havina Number Name m apertm thelfithrou h corresponding to 33m B65373 Budd Jan 15 1901 central aperture to provide a cooling fluid inlet 752,340 Hohwarth Feb.
Description
y 3, 1951 H. OESTRICH EI'AL 2,559,131
HOLLOW BLADE FOR GAS TURBINES AND THE LIKE Filed April 11. 1949 s sheets-sheet 1 y-1 Fig.3
IIIIII/IIIIIIIIIIIIIIIIIIIIII!Ir r; u- 4 July 3', 1951 H. OESTRICH EIAL HOLLOW BLADE FOR GAS TURBINES AND THE LIKE Filed April 11. 1949 3 Sheets-Sheet 2 s Sheets-Sheet 3 HOLLOW BLADE FOR GAS TURBINES AND THE LIKE July 3, 1951 Filed April 11, 1949 Patented July 3, 1951 HOLLOW nuns Foa GAS 'rnnamss AND run-mm Hermann Oestrich, Hans Rosskopf, Alfred Renner, and Jakob ValteaDecize, France; said Rosskopf, said Renner, and said Valter assignors to said Oestrich Application April 11, 1949, Serial No. 86,703
In France April 22, 1948 Our invention has for its object a hollow blade cooled from the inside and preferably executed by means of a blank of sheet metal that is intended for gas turbines and the like machines operating with a flow of fluid.
In all blades of this type known to this day. the securing of a blade to a blade carrier, such as a turbine wheel is executed by means of wedging pins or keys or again through the engagement in zig-zag grooves of'wedging members or of suitable shaped parts.
The cooling fluid is introduced either laterally through ports provided in the vicinity of the root of the blade on the leading edge and the trailing edge of the latter or again through a recess provided between the root of the blade and the blade carrier, said recess being provided in one side of theroot assuming the shape of a case, which I side extends beyond the blade carrier. In both cases, the channels feeding the blades communicate with a chamber formed by a covering metal sheet and the blade carrier and into which is introduced the cooling fluid.
The drawbacks of known blades of this type consist in that they hardly satisfy the conditions of mechanical resistance and of secure fixation that are necessary for turbine blades, that the root of the blade and corresponding recess in the blade carrier are of a comparatively dimcult execution, that the securing inside the blade of the diaphragm intended for instance for the guiding of the cooling medium is a difficult matter, that the blades are interchangeable with some difllculty and the introduction of the cooling fluid into the blade leads to considerable losses by reason of the marked bands of the circuit and unavoidable losses.
The object of the invention is to provide a hollow blade that allows removing the above drawbacksand also the execution of a blade root, starting from a single blank of sheet metal. This is obtained by forming the blade in the following manner:
The metal sheet forming the wall of the blade is bent at one end so as to form the root, the cross-section of which assumes preferably the shape of a segment of a circle. The connection between the root and the body of the blade is performed at the ends of said segment along both sides of the bent blade through a plane 13 Claims. (01. 60-41) surface that provides together with the root for the fitting and guiding of the blade over the turbine wheel. The root is reinforced by an inserted pin and shows at its lower end one or more openings intended for the axial passage of the cooling fluid from the turbine wheel.
The hollow blade forming the object of the invention includes therefore a Laval type or similar root, that is well known per se and has proved satisfactory for solid blades.
The following description and accompanying drawings given by way of example and by no means in a binding sense will allow understanding how the invention may be executed, the features appearing in the drawings and in the specification forming obviously part of said invention. In said drawings:
Fig. 1 is a lateral elevational view of a hollow blade according to the invention.
Fig. 2 is 'a cross-section on a larger scale through line AA of Fig. 1.
Fig. 3 is a cross-section through line BB of Fig. 2.
Fig. 4 illustrates a modified shape that may be given to the trailing edge of the blade.
Figs. 5, 6 and 7 illustrate respectively in elevational view, in cross-sectional view and in longi- 'tudinal section a flat blank of sheet metal used for executing the blade.
Figs. 8 and 9 illustrate a manner of mounting the blade according to the invention on a turbine rotor. Fig. 8 is a partial elevational view of the rotor seen from the side corresponding to the leading edge while Fig. 9 is a crosssection through line 12-13 of Fig. 8.
The blade shown in Figs. 1 to 3 is obtained through the folding inside dies, by means of shaped tools, of a flat blank of sheet metal as illustrated in Figs. 5, 6 and 7. One end of the the joining surface at the lower end of the root between the lugs 1a and lb forming said root and that are welded together along said joining surface 6. The pin 4 is welded to the sheet metal forming the blade at both ends of said spindle and along the joining surface 6. In the example illustrated, the welding seam 8 provided on the side corresponding to the leading edge of the blade extends throughout the periphery of the pin 4 while the welding for the side corresponding to the trailing edge of the blade extends only over the lower half of the root for reasons of mechanical resistance. For similar reasons, the welding seam closing the body I of the blade extends over the trailing edge 10 only up to a point ll (Fig. 1) From this standpoint, it should be remarked that it is also possible to weld the pin 4 to the sheet metal forming the blade I and also to weld the latter along the joint 6 and further to weld the trailing edge It] in a manner such that the blade may be hermetically sealed throughout its surface except for the opening 5 provided in the root for the introduction of the cooling fluid and also for the opening provided for the output of said cooling fluid that is preferably provided at the tip of said blade.
In register with the opening 5, the pin 4 assumes a lesser cross-section so that the cooling fluid may pass into the inside of the blade to either side of the reduced pin portion 40. along the direction illustrated by the arrows. The crosssection of the reduced part of the pin may be given any desired shape. Instead of reducing the diameter of the pin, it is also possible to provide a gap in it or to perforate it in register with the opening 5. Preferably, the pin may be constituted by two separate members that are fitted into the root through the opposed ends thereof.
When the blade includes as in the embodiment illustrated a diaphragm l2 that serves for guiding the cooling air or for damping the vibrations or again simultaneously for both purposes said diaphragm' 12 engages the slot I3 of the pin 4 and extends into the lower end of the root where it is welded to the pin 4.
The root illustrated that has a transversal cross-section in the shape of a circular sector may be replaced by a-root of any desired crosssection that may be for instance square, rectanguerated through points or along a continuous line.
The starting material used for producing the blade through a folding of a flat sheet of metal is constituted according to the invention by a blank l5 cut to the desired shape as illustrated in Figs. 5, 6 and '7. When flat, said blank appears substantially as a rectangular member provided at one end with four rectangular lugs, l6-l1--l8-l9 adapted to'form the root of the blade. The size and spacing of the lugs are defined by the size of the openings to be provided in the root and by the diameter of the latter. It is preferable to make use of a metal sheet the thickness of which gradually decreases from the root towards the tip of the blade as illustrated in Fig. 7, that is a cross-section through line D-D of Fig. 5. The two edges Illa and lb of the blank that are to bear against one another after folding so as to form the trailing edge ll) of the blade are bevelled on their inner side in the manner illustrated in Fig. 6, that is a cross-section through line C-C of Fig. 5.
Preferably the depth of the bevel diminishes gradually from the root towards the tip of the blade as shown in dotted lines at 20a. and 20b in Fig. 5.
In order to provide for the shaping of the blank with a. decreasing thickness and possibly also with a bevelled edge, it is of advantage to use for instance rolling mill rolls inside which the desired .section is machined.
In order to produce the blade assuming the shape according to the invention, it is possible to use inplace of the flat sheet metal blank as disclosed a socket or. tube-shaped member that is stamped or drawn to the desired shape.
In the manner of mounting the blade according to the invention on a turbine wheel as illustrated in Figs. 8 and 9, said blade is fitted in corresponding grooves 2| or the rim 22. The reference number 23 designates the disc of the wheel carrying the blades while .24 designates a locking ring engaging the grooves [4 of the different blades, 25 a balancing member and 26 one of the channels provided through the rim 22 and through which the cooling fluid is fed to the blade or to the openings 5 provided in the root of the blades and progressing in the direction of the arrows. Fig. 8 shows in interrupted lines three such channels 26 that receive the cooling fluid from the chamber 21 formed by the disc 23, the rim 22 and the cover 28. This cooling fluid is fed to said chamber through suitable ducts that are not illustrated.
As illustrated in Fig. 9, the cooling fluid is admitted into the blade and flows through same without any sharp turns and the channelling system shows no leaking point.
Obviously various modifications may be brought to the hollow blade that has just been described in particular through substitution of equivalent technical means for those referred to without unduly widening thereby the scope of the invention as defined in accompanying claims.
What we claim is: l
1. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body atthe root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to saidhollow body.
2. An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body 3. an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, flat portions being provided between said body and the bent part of said lugs, said flat portions being parallel with one another and spaced by a distance less than the maximal width of said tubular assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
5. An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a cylindrical tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
6. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, a welded seam being provided between the abutted ends of said lugs at the lower part of said root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
7. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, a welded seam being provided between the abutted ends of said lugs at the lower part of said root assembly; and a pin fltted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body, said pin being welded to said lugs along said welded seam and at its ends.
8. In an inwardly cooled blade for gas turbines or the, like machines having a hollow sheet m'etalbody through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fltted in said assembly, said assembly having an aperture therethrough and said pin having a reduced cross-section in register with said aperture to provide a cooling fluid inlet passage to said hollow body.
9. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly having an aperture therethrough and said pin including two parts separated by a gap registering with said aperture to provide a cooling fluid inlet passage to said hollow body.
10. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; a pin provided with a diametrical slot fitted in said assembly and a metal sheet diaphragm located longitudinally inside the blade and including an extension engaging said slot in said pin and welded to said pin, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
. 11. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof,-said lugs being bent with their outer ends in abutting relationship so as to form a cylindrical tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
12. In an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a polygonal tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
13. An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length; two pairs of spaced lugs projecting from said hollow body at the root end of the front and rear part thereof respectively, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly 7 provided with a central aperture therethrouth; UNITED STATES PATENTS and a pin fitted in said assembly, said pin havina Number Name m apertm thelfithrou h corresponding to 33m B65373 Budd Jan 15 1901 central aperture to provide a cooling fluid inlet 752,340 Hohwarth Feb. 16 1904 P 8 to said W i 1,200,775 swinger June 4, 191a 1,530,249 Eveleth Mar. 1'7. 1925 HERMAN OESTRICH- 1,001,402 Lorenzen Sept. 2a, 1920 ms ROSSKOPF- 2,220,420 Meyer Nov. 5, 1940 ALFRED RENNER- 2,251,920 Erb m Aug. 12, 1941 JAKQB 'F l0 2,297,440 Zellbeck Sept. 29, 1942 2:93:: 22: 12:: 2; o y REFERENCES CITED 2,459,429 Jacobi Jan. 18, 1949 The following references are of record in the 2,482,990 Olson Sept. 2'7, 1949 Nuinber Country Date 359,349 Great Britain Oct. 22, 1931
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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FR664938X | 1948-04-22 |
Publications (1)
Publication Number | Publication Date |
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US2559131A true US2559131A (en) | 1951-07-03 |
Family
ID=9012978
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US86703A Expired - Lifetime US2559131A (en) | 1948-04-22 | 1949-04-11 | Hollow blade for gas turbines and the like |
Country Status (5)
Country | Link |
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US (1) | US2559131A (en) |
DE (1) | DE855178C (en) |
FR (1) | FR965814A (en) |
GB (1) | GB664938A (en) |
IT (1) | IT454293A (en) |
Cited By (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2642263A (en) * | 1951-01-05 | 1953-06-16 | Westinghouse Electric Corp | Blade apparatus |
US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2699584A (en) * | 1950-02-28 | 1955-01-18 | Woodworth Ind Process Company | Flint tube mold and method of making the same |
US2708564A (en) * | 1952-02-29 | 1955-05-17 | Westinghouse Electric Corp | Turbine apparatus |
US2719294A (en) * | 1953-02-17 | 1955-10-04 | Wilson Jones Co | Staple gun tacker |
US2762114A (en) * | 1951-08-28 | 1956-09-11 | Gen Motors Corp | Method of making sheet metal turbine bucket |
US2772851A (en) * | 1950-06-14 | 1956-12-04 | Stalker Dev Company | Rotor construction |
US2783023A (en) * | 1950-04-05 | 1957-02-26 | Stalker Dev Company | Fluid rotor having damping means |
US2801073A (en) * | 1952-06-30 | 1957-07-30 | United Aircraft Corp | Hollow sheet metal blade or vane construction |
US2801072A (en) * | 1949-11-22 | 1957-07-30 | Hermann Oestrich | Hollow blade for fluid flow operated machine |
US2809802A (en) * | 1952-09-10 | 1957-10-15 | Gen Electric | Damping turbine blades |
US2823889A (en) * | 1950-04-05 | 1958-02-18 | Stalker Dev Company | Rotor construction and fabrication |
US2828940A (en) * | 1953-12-30 | 1958-04-01 | United Aircraft Corp | Cooled turbine blade |
US2849209A (en) * | 1950-10-11 | 1958-08-26 | Gen Electric | Nozzle construction for turbines |
US2859011A (en) * | 1953-07-27 | 1958-11-04 | Gen Motors Corp | Turbine bucket and liner |
US2863633A (en) * | 1952-04-19 | 1958-12-09 | Stalker Dev Company | Hollow blades and manufacture thereof |
US2869611A (en) * | 1955-03-18 | 1959-01-20 | Stalker Dev Company | Apparatus including a female die receiving a reciprocating articulated male die for stretch-forming hollow blades |
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
US2875948A (en) * | 1953-01-19 | 1959-03-03 | Stalker Dev Company | Thin wall bladed wheels for axial flow machines |
US2916808A (en) * | 1955-03-28 | 1959-12-15 | Gen Electric | Method of making a blade for turbomachines |
US2954208A (en) * | 1953-01-09 | 1960-09-27 | Gen Motors Corp | Air foil section |
US2976014A (en) * | 1952-01-19 | 1961-03-21 | Bbc Brown Boveri & Cie | Blading for use in axial flow machines |
US2979809A (en) * | 1956-03-14 | 1961-04-18 | Napier & Son Ltd | Method of making hollow turbine blades |
US3002265A (en) * | 1957-02-14 | 1961-10-03 | Stalker Corp | Fabrication of blades for compressors and the like |
US3010696A (en) * | 1955-09-26 | 1961-11-28 | Rolls Royce | Bladed rotor with means to supply fluid to passages in the blades |
US3023998A (en) * | 1959-03-13 | 1962-03-06 | Jr Walter H Sanderson | Rotor blade retaining device |
US3027138A (en) * | 1951-12-10 | 1962-03-27 | Power Jets Res & Dev Ltd | Turbine blades |
US3039739A (en) * | 1958-11-28 | 1962-06-19 | Gen Motors Corp | Pinned blade connecting means |
US3045967A (en) * | 1952-04-12 | 1962-07-24 | Stalker Corp | Hollow blades and manufacture thereof |
US3083446A (en) * | 1950-06-14 | 1963-04-02 | Stalker Corp | Rotor construction |
US3388888A (en) * | 1966-09-14 | 1968-06-18 | Gen Electric | Cooled turbine nozzle for high temperature turbine |
US3697192A (en) * | 1970-05-07 | 1972-10-10 | United Aircraft Corp | Hollow turbine blade |
US3747182A (en) * | 1970-05-07 | 1973-07-24 | United Aircraft Corp | Method of fabricating a hollow turbine blade having an insert therein |
US4037990A (en) * | 1976-06-01 | 1977-07-26 | General Electric Company | Composite turbomachinery rotor |
US5022824A (en) * | 1988-10-07 | 1991-06-11 | United Technologies Corporation | Pinned airfoil propeller blade |
US5022825A (en) * | 1988-10-07 | 1991-06-11 | United Technologies Corporation | Pitch retention member |
US5102300A (en) * | 1988-10-07 | 1992-04-07 | United Technologies Corporation | Pinned airfoil propeller assembly |
US5205714A (en) * | 1990-07-30 | 1993-04-27 | General Electric Company | Aircraft fan blade damping apparatus |
US6283707B1 (en) * | 1999-03-19 | 2001-09-04 | Rolls-Royce Plc | Aerofoil blade damper |
JP2013072333A (en) * | 2011-09-27 | 2013-04-22 | Mitsubishi Heavy Ind Ltd | Stator blade and steam turbine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE944645C (en) * | 1952-08-08 | 1956-06-21 | Max Adolf Mueller Dipl Ing | Rotary rotor for rotary feeders for gas turbines and jet engines |
US2853272A (en) * | 1952-09-12 | 1958-09-23 | Napier & Son Ltd | Hollow blades for turbo machines |
JP4355396B2 (en) | 1999-06-04 | 2009-10-28 | 富士フイルムファインケミカルズ株式会社 | Method for producing diarylamine |
FR3087484B1 (en) * | 2018-10-18 | 2021-01-15 | Safran Aircraft Engines | TURBOMACHINE DAWN |
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US665873A (en) * | 1900-06-02 | 1901-01-15 | American Pulley Co | Sheet-metal spoke-blank. |
US752340A (en) * | 1904-04-16 | A corpora | ||
US1268775A (en) * | 1917-04-11 | 1918-06-04 | Nathan Stanger | Bail-guard. |
US1530249A (en) * | 1922-09-23 | 1925-03-17 | Gen Electric | Turbine bucket |
US1601402A (en) * | 1921-01-15 | 1926-09-28 | Lorenzen Christian | Gas turbine |
GB359349A (en) * | 1930-03-03 | 1931-10-22 | Ltd Co Formerly Skoda Works | Method of producing a hollow blade for steam and gas turbines |
US2220420A (en) * | 1938-02-08 | 1940-11-05 | Bbc Brown Boveri & Cie | Means for cooling machine parts |
US2251926A (en) * | 1939-05-18 | 1941-08-12 | American Can Co | Container |
US2297446A (en) * | 1938-12-03 | 1942-09-29 | Zellbeck Gustav | Hollow blade for exhaust gas turbine rotors |
US2357628A (en) * | 1944-09-05 | Blade | ||
US2409966A (en) * | 1942-01-14 | 1946-10-22 | Universal Slide Fastener Co In | Blank for use in the manufacture of sliders for slide fasteners |
US2459428A (en) * | 1945-04-19 | 1949-01-18 | Briggs & Stratton Corp | Air cleaner |
US2482990A (en) * | 1948-02-09 | 1949-09-27 | Sealed Power Corp | Piston ring blank |
Family Cites Families (5)
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DE522992C (en) * | 1928-09-27 | 1931-04-22 | Vladimir Kalabek | Multi-stage gas turbine in which the gaseous coolant is used for work |
DE557860C (en) * | 1930-01-17 | 1932-08-29 | Lorenzen G M B H C | Runner consisting of two discs for gas turbines and centrifugal compressors |
DE737479C (en) * | 1939-01-26 | 1943-07-15 | Versuchsanstalt Fuer Luftfahrt | Gas turbine blade |
DE735668C (en) * | 1940-04-26 | 1943-05-21 | Maschf Augsburg Nuernberg Ag | Gas turbine wheel made of ceramic material |
DE724470C (en) * | 1940-10-20 | 1942-08-27 | Versuchsanstalt Fuer Luftfahrt | Internally cooled gas turbine blade |
-
0
- IT IT454293D patent/IT454293A/it unknown
- FR FR965814D patent/FR965814A/fr not_active Expired
-
1949
- 1949-04-11 US US86703A patent/US2559131A/en not_active Expired - Lifetime
- 1949-04-12 GB GB9903/49A patent/GB664938A/en not_active Expired
- 1949-10-29 DE DEO65A patent/DE855178C/en not_active Expired
Patent Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2357628A (en) * | 1944-09-05 | Blade | ||
US752340A (en) * | 1904-04-16 | A corpora | ||
US665873A (en) * | 1900-06-02 | 1901-01-15 | American Pulley Co | Sheet-metal spoke-blank. |
US1268775A (en) * | 1917-04-11 | 1918-06-04 | Nathan Stanger | Bail-guard. |
US1601402A (en) * | 1921-01-15 | 1926-09-28 | Lorenzen Christian | Gas turbine |
US1530249A (en) * | 1922-09-23 | 1925-03-17 | Gen Electric | Turbine bucket |
GB359349A (en) * | 1930-03-03 | 1931-10-22 | Ltd Co Formerly Skoda Works | Method of producing a hollow blade for steam and gas turbines |
US2220420A (en) * | 1938-02-08 | 1940-11-05 | Bbc Brown Boveri & Cie | Means for cooling machine parts |
US2297446A (en) * | 1938-12-03 | 1942-09-29 | Zellbeck Gustav | Hollow blade for exhaust gas turbine rotors |
US2251926A (en) * | 1939-05-18 | 1941-08-12 | American Can Co | Container |
US2409966A (en) * | 1942-01-14 | 1946-10-22 | Universal Slide Fastener Co In | Blank for use in the manufacture of sliders for slide fasteners |
US2459428A (en) * | 1945-04-19 | 1949-01-18 | Briggs & Stratton Corp | Air cleaner |
US2482990A (en) * | 1948-02-09 | 1949-09-27 | Sealed Power Corp | Piston ring blank |
Cited By (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2801072A (en) * | 1949-11-22 | 1957-07-30 | Hermann Oestrich | Hollow blade for fluid flow operated machine |
US2699584A (en) * | 1950-02-28 | 1955-01-18 | Woodworth Ind Process Company | Flint tube mold and method of making the same |
US2783023A (en) * | 1950-04-05 | 1957-02-26 | Stalker Dev Company | Fluid rotor having damping means |
US2823889A (en) * | 1950-04-05 | 1958-02-18 | Stalker Dev Company | Rotor construction and fabrication |
US2772851A (en) * | 1950-06-14 | 1956-12-04 | Stalker Dev Company | Rotor construction |
US3083446A (en) * | 1950-06-14 | 1963-04-02 | Stalker Corp | Rotor construction |
US2849209A (en) * | 1950-10-11 | 1958-08-26 | Gen Electric | Nozzle construction for turbines |
US2642263A (en) * | 1951-01-05 | 1953-06-16 | Westinghouse Electric Corp | Blade apparatus |
US2762114A (en) * | 1951-08-28 | 1956-09-11 | Gen Motors Corp | Method of making sheet metal turbine bucket |
US3027138A (en) * | 1951-12-10 | 1962-03-27 | Power Jets Res & Dev Ltd | Turbine blades |
US2976014A (en) * | 1952-01-19 | 1961-03-21 | Bbc Brown Boveri & Cie | Blading for use in axial flow machines |
US2708564A (en) * | 1952-02-29 | 1955-05-17 | Westinghouse Electric Corp | Turbine apparatus |
US3045967A (en) * | 1952-04-12 | 1962-07-24 | Stalker Corp | Hollow blades and manufacture thereof |
US2863633A (en) * | 1952-04-19 | 1958-12-09 | Stalker Dev Company | Hollow blades and manufacture thereof |
US2801073A (en) * | 1952-06-30 | 1957-07-30 | United Aircraft Corp | Hollow sheet metal blade or vane construction |
US2809802A (en) * | 1952-09-10 | 1957-10-15 | Gen Electric | Damping turbine blades |
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
US2954208A (en) * | 1953-01-09 | 1960-09-27 | Gen Motors Corp | Air foil section |
US2875948A (en) * | 1953-01-19 | 1959-03-03 | Stalker Dev Company | Thin wall bladed wheels for axial flow machines |
US2719294A (en) * | 1953-02-17 | 1955-10-04 | Wilson Jones Co | Staple gun tacker |
US2859011A (en) * | 1953-07-27 | 1958-11-04 | Gen Motors Corp | Turbine bucket and liner |
US2828940A (en) * | 1953-12-30 | 1958-04-01 | United Aircraft Corp | Cooled turbine blade |
US2869611A (en) * | 1955-03-18 | 1959-01-20 | Stalker Dev Company | Apparatus including a female die receiving a reciprocating articulated male die for stretch-forming hollow blades |
US2916808A (en) * | 1955-03-28 | 1959-12-15 | Gen Electric | Method of making a blade for turbomachines |
US3010696A (en) * | 1955-09-26 | 1961-11-28 | Rolls Royce | Bladed rotor with means to supply fluid to passages in the blades |
US2979809A (en) * | 1956-03-14 | 1961-04-18 | Napier & Son Ltd | Method of making hollow turbine blades |
US3002265A (en) * | 1957-02-14 | 1961-10-03 | Stalker Corp | Fabrication of blades for compressors and the like |
US3039739A (en) * | 1958-11-28 | 1962-06-19 | Gen Motors Corp | Pinned blade connecting means |
US3023998A (en) * | 1959-03-13 | 1962-03-06 | Jr Walter H Sanderson | Rotor blade retaining device |
US3388888A (en) * | 1966-09-14 | 1968-06-18 | Gen Electric | Cooled turbine nozzle for high temperature turbine |
US3747182A (en) * | 1970-05-07 | 1973-07-24 | United Aircraft Corp | Method of fabricating a hollow turbine blade having an insert therein |
US3697192A (en) * | 1970-05-07 | 1972-10-10 | United Aircraft Corp | Hollow turbine blade |
US4037990A (en) * | 1976-06-01 | 1977-07-26 | General Electric Company | Composite turbomachinery rotor |
US5022824A (en) * | 1988-10-07 | 1991-06-11 | United Technologies Corporation | Pinned airfoil propeller blade |
US5022825A (en) * | 1988-10-07 | 1991-06-11 | United Technologies Corporation | Pitch retention member |
US5102300A (en) * | 1988-10-07 | 1992-04-07 | United Technologies Corporation | Pinned airfoil propeller assembly |
US5205714A (en) * | 1990-07-30 | 1993-04-27 | General Electric Company | Aircraft fan blade damping apparatus |
US6283707B1 (en) * | 1999-03-19 | 2001-09-04 | Rolls-Royce Plc | Aerofoil blade damper |
GB2347975B (en) * | 1999-03-19 | 2003-01-22 | Rolls Royce Plc | Aerofoil blade damper |
JP2013072333A (en) * | 2011-09-27 | 2013-04-22 | Mitsubishi Heavy Ind Ltd | Stator blade and steam turbine |
Also Published As
Publication number | Publication date |
---|---|
IT454293A (en) | |
FR965814A (en) | 1950-09-22 |
GB664938A (en) | 1952-01-16 |
DE855178C (en) | 1952-11-10 |
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