US2906089A - Air intake control for jet propulsion units - Google Patents

Air intake control for jet propulsion units Download PDF

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Publication number
US2906089A
US2906089A US35866653A US2906089A US 2906089 A US2906089 A US 2906089A US 35866653 A US35866653 A US 35866653A US 2906089 A US2906089 A US 2906089A
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United States
Prior art keywords
air intake
jet propulsion
propulsion units
intake control
air
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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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Inventor
Kadosch Marcel
Jean H Bertin
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Safran Aircraft Engines SAS
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SNECMA SAS
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Application filed by SNECMA SAS filed Critical SNECMA SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/32—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for reversing thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/04—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with resonant combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/06—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
    • F02K7/067—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves having aerodynamic valves
    • 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
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

  • the present invention relates to the control of air intakes of jet propulsion unit.
  • An object of this invention is to provide aerodynamically operating means for varying the effective area and outline of an air intake casing without requiring displacement of movable members in said air intake.
  • a further object of this invention is to adapt the air intake to various flight conditions.
  • the invention enables the cross-section of the air intake passage and/or its internal shape to be varied according to whether the speed of travel through the air is subsonic or supersonic.
  • the auxiliary jet When the auxiliary jet is not in operation, the full physical cross-section of the air intake passage is available for the quantity of air passing into the reaction unit, which is satisfactory for flight at low speed.
  • this auxiliary jet when the auxiliary jet is blown into the air intake opening, this auxiliary jet causes a fluid wall to be substituted for the solid wall of the air intake passage, so that the cross-section available for the air drawn in is reduced.
  • the fluid wall takes, in its proper flow, the form of a convergent-divergent fluid dischargenozzle and the passage of the air intake is thus adapted to supersonic flight.
  • the fairing 1 of the air intake of a reaction unit which is supposed in this example to be a ram-jet unit, surrounds a streamlined body 2 such that the general outline, from the forward end up to the neighborhood of the maximum cross-section of this streamlined body, is slightly convergent, only to become later more strongly divergent up to the combustion chamber 3.
  • Blowing slots extended at 4 on the internal periphery of the fairing, and at 5 on the external periphery of the streamlined body. These slots are so shaped as to expand the fluid which passes through them, thus producing a jet at a high dynamic pressure.
  • the slots may have a convergentdivergent form; they are arranged at the beginning of the divergent portion of the reactor air intake and may be supplied with a suitable auxiliary fluid having a total pressure greater than the static pressure of the air flowing through the intake opening of the reaction unit.
  • the slots may be supplied, for example, with compressed air obtained from a small compressor 3a driven by a suitable auxiliary engine, for example by a gas turbine 3b.
  • the supply of air to the slots is controlled by a valve 7.
  • the slots When the flow of air in front of the ram-jet unit is subsonic, the slots are not supplied with air and the air intake opening is divergent. When the flow is supersonic, the slots are supplied with compressed air and there is thus obtained a convergent-divergent discharge-nozzle by the action of the blowing jet or jets (along the arrows shown at the top) which constitute fluid walls the shape of which may be varied at will and which permit the presence of a subsonic flow at the point at which the main flow becomes divergent.
  • an aerodynamically-operating device for adapting said air intake to supersonic flow, comprising a circular slotlike nozzle extending through each of said walls and opening towards the interior of said air intake in a forwardly inclined direction, said slot-like nozzles being substantially opposite each other, and controllable means for supplying pressure fluid to said nozzles to form screenlike jets projecting into said intake from said walls whereby a convergent-divergent duct with fluid walls is substi tuted for said divergent passage with physical walls.

Description

Sept. 29, 1959 M. KADOSCH ET AL AIR INTAKE CONTROL FOR JET PROPULSION UNITS Filed June 1, 1953 6 w I [fr t MI WW flTTORNEYs United States Patent AIR INTAKE CONTROL FOR JET PROPULSION UNITS Marcel Kadosch, Paris, and Jean H. Bertln, Neuilly-sur- Seine, France, assignors to Societe Nationale dEtude et de Construction de Moteurs dAviation, Paris, France, a French company Application June 1, 1953, Serial No. 358,666
Claims priority, application France June 5, 1952 1 Claim. (Cl. till-35.6)
The present invention relates to the control of air intakes of jet propulsion unit.
An object of this invention is to provide aerodynamically operating means for varying the effective area and outline of an air intake casing without requiring displacement of movable members in said air intake.
A further object of this invention is to adapt the air intake to various flight conditions.
According to one of its forms of embodiment, the invention enables the cross-section of the air intake passage and/or its internal shape to be varied according to whether the speed of travel through the air is subsonic or supersonic. When the auxiliary jet is not in operation, the full physical cross-section of the air intake passage is available for the quantity of air passing into the reaction unit, which is satisfactory for flight at low speed. On the other hand, when the auxiliary jet is blown into the air intake opening, this auxiliary jet causes a fluid wall to be substituted for the solid wall of the air intake passage, so that the cross-section available for the air drawn in is reduced. In addition, the fluid wall takes, in its proper flow, the form of a convergent-divergent fluid dischargenozzle and the passage of the air intake is thus adapted to supersonic flight.
In the accompanying drawing, the single figure is a longitudinal section of an air intake casing arranged in accordance with the invention.
In this figure, the fairing 1 of the air intake of a reaction unit, which is supposed in this example to be a ram-jet unit, surrounds a streamlined body 2 such that the general outline, from the forward end up to the neighborhood of the maximum cross-section of this streamlined body, is slightly convergent, only to become later more strongly divergent up to the combustion chamber 3. Blowing slots extended at 4 on the internal periphery of the fairing, and at 5 on the external periphery of the streamlined body. These slots are so shaped as to expand the fluid which passes through them, thus producing a jet at a high dynamic pressure. The slots may have a convergentdivergent form; they are arranged at the beginning of the divergent portion of the reactor air intake and may be supplied with a suitable auxiliary fluid having a total pressure greater than the static pressure of the air flowing through the intake opening of the reaction unit. The slots may be supplied, for example, with compressed air obtained from a small compressor 3a driven by a suitable auxiliary engine, for example by a gas turbine 3b. The supply of air to the slots is controlled by a valve 7.
When the flow of air in front of the ram-jet unit is subsonic, the slots are not supplied with air and the air intake opening is divergent. When the flow is supersonic, the slots are supplied with compressed air and there is thus obtained a convergent-divergent discharge-nozzle by the action of the blowing jet or jets (along the arrows shown at the top) which constitute fluid walls the shape of which may be varied at will and which permit the presence of a subsonic flow at the point at which the main flow becomes divergent.
What we claim is:
In a jet propulsion unit designed to operate both in the subsonic and in the supersonic range and having a forwardly opening air intake bounded by two walls, an outer wall and an inner wall, defining a generally divergent passage whose outline is designed for subsonic flow, an aerodynamically-operating device for adapting said air intake to supersonic flow, comprising a circular slotlike nozzle extending through each of said walls and opening towards the interior of said air intake in a forwardly inclined direction, said slot-like nozzles being substantially opposite each other, and controllable means for supplying pressure fluid to said nozzles to form screenlike jets projecting into said intake from said walls whereby a convergent-divergent duct with fluid walls is substi tuted for said divergent passage with physical walls.
References Cited in the file of this patent UNITED STATES PATENTS 2,409,433 Hunter Oct. 15, 1946 2,570,629 Anxionnaz et al Oct. 9, 1951 2,577,919 Roy Dec. 11, 1951 2,612,749 Tenney et a1 Oct. 7, 1952 2,628,473 Frye Feb. 17, 1953 2,631,425 Nordfors Mar. 17, 1953 2,632,295 Price Mar. 24, 1953 2,663,993 Mosser Dec. 29, 1953 2,692,800 Nichols et al Oct. 26, 1954 2,705,863 Clark et al. Apr. 12, 1955 2,763,984 Kadosch et al. Sept. 25, 1956 FOREIGN PATENTS 503,064 Belgium May 31, 1951 50,033 France Aug. 1, 1939 (3rd addition tof No. 779,655)
439,805 Great Britain Dec. 6, 1935 444,103 Great Britain Mar. 13, 1936 OTHER REFERENCES Aero Digest, vol. 60, No. 4, April 1950, see the Chandler article on pages -102.
US35866653 1951-01-04 1953-06-01 Air intake control for jet propulsion units Expired - Lifetime US2906089A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR970090X 1951-01-04
FR767513X 1952-12-12

Publications (1)

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DE (1) DE970090C (en)
FR (3) FR1030483A (en)
GB (2) GB757496A (en)

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US3047208A (en) * 1956-09-13 1962-07-31 Sebac Nouvelle Sa Device for imparting movement to gases
US3086357A (en) * 1959-04-30 1963-04-23 Mithras Inc Supersonic flow control device
US3259065A (en) * 1959-04-30 1966-07-05 Massachusetts Inst Technology Shock wave inducing means for supersonic vehicles
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US3966355A (en) * 1975-06-24 1976-06-29 Westinghouse Electric Corporation Steam turbine extraction system
US4161281A (en) * 1976-08-30 1979-07-17 Erb Elisha Pneumatic nebulizer and method
US4261511A (en) * 1978-08-07 1981-04-14 Erb Elisha Nebulizer and method
US6260567B1 (en) * 1997-07-22 2001-07-17 The Boeing Company Mission adaptive inlet
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
US20090165864A1 (en) * 2007-12-26 2009-07-02 Rolls-Royce North American Technologies, Inc. Supersonic inlet
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US2663993A (en) * 1945-10-10 1953-12-29 Westinghouse Electric Corp Deicing apparatus
US2612749A (en) * 1946-04-11 1952-10-07 Tenney Resonant pulse jet device with restricted flow passage
US2577919A (en) * 1947-07-22 1951-12-11 Snecma Association on flying machine of compressor-jet units with ramjet units
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US2631425A (en) * 1948-09-11 1953-03-17 Bofors Ab Compression nozzle for ram-jet engines
US2705863A (en) * 1950-06-30 1955-04-12 Curtiss Wright Corp Jet engine with adjustable air inlet capture area
BE503064A (en) * 1951-05-10 1900-01-01
US2692800A (en) * 1951-10-08 1954-10-26 Gen Electric Nozzle flow control
US2763984A (en) * 1954-09-17 1956-09-25 Snecma Device for regulating the effective cross-section of a discharge-nozzle

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3047208A (en) * 1956-09-13 1962-07-31 Sebac Nouvelle Sa Device for imparting movement to gases
US3086357A (en) * 1959-04-30 1963-04-23 Mithras Inc Supersonic flow control device
US3259065A (en) * 1959-04-30 1966-07-05 Massachusetts Inst Technology Shock wave inducing means for supersonic vehicles
US3446223A (en) * 1966-02-04 1969-05-27 Lockheed Aircraft Corp Air intake for gas turbine engines
US3623668A (en) * 1968-03-04 1971-11-30 Gen Electric Wash manifold
US3643901A (en) * 1970-05-27 1972-02-22 Isidor C Patapis Ducted spike diffuser
US3966355A (en) * 1975-06-24 1976-06-29 Westinghouse Electric Corporation Steam turbine extraction system
US4161282A (en) * 1976-08-30 1979-07-17 Erb Elisha Microcapillary nebulizer and method
US4161281A (en) * 1976-08-30 1979-07-17 Erb Elisha Pneumatic nebulizer and method
US4261511A (en) * 1978-08-07 1981-04-14 Erb Elisha Nebulizer and method
US6260567B1 (en) * 1997-07-22 2001-07-17 The Boeing Company Mission adaptive inlet
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
JP2009002336A (en) * 2007-06-20 2009-01-08 General Electric Co <Ge> Thrust generator for propulsion system
US20090165864A1 (en) * 2007-12-26 2009-07-02 Rolls-Royce North American Technologies, Inc. Supersonic inlet
US20090288711A1 (en) * 2008-05-21 2009-11-26 Alvi Farrukh S Microjet creation and control of shock waves
US8359825B2 (en) * 2008-05-21 2013-01-29 Florida State University Research Foundation Microjet creation and control of shock waves
US20160052621A1 (en) * 2009-07-10 2016-02-25 Peter Ireland Energy efficiency improvements for turbomachinery
US20140248119A1 (en) * 2012-10-01 2014-09-04 United Technologies Corporation Bifurcated Inlet Scoop for Gas Turbine Engine
US10385777B2 (en) * 2012-10-01 2019-08-20 United Technologies Corporation Bifurcated inlet scoop for gas turbine engine

Also Published As

Publication number Publication date
DE970090C (en) 1958-08-21
FR62595E (en) 1955-06-15
FR63348E (en) 1955-09-13
GB767513A (en) 1957-02-06
FR1030483A (en) 1953-06-15
GB757496A (en) 1956-09-19

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