CN105443162A - Engine transition section and aero-engine - Google Patents
Engine transition section and aero-engine Download PDFInfo
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- CN105443162A CN105443162A CN201410499761.6A CN201410499761A CN105443162A CN 105443162 A CN105443162 A CN 105443162A CN 201410499761 A CN201410499761 A CN 201410499761A CN 105443162 A CN105443162 A CN 105443162A
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- end wall
- transition section
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Abstract
The invention discloses an engine transition section and an aero-engine, and relates to the technical field of aero-engines. The technical problem that the aerodynamic performance of a transition section in the prior art is poor is solved. The engine transition section comprises an outer end wall, an inner end wall and a supporting plate arranged between the outer end wall and the inner end wall; the supporting plate is provided with an air flow passage penetrating through the supporting plate; air flow flowing through a pressure surface of the supporting plate passes through the air flow passage towards a suction surface of the supporting plate and drives low-energy fluid around the suction surface to flow towards the lower stream. The aero-engine comprises the engine transition section provided by the technical scheme, the outer end wall is the inner surface of a peripheral machine case, and the inner end wall is the outer surface of a hub. According to the invention, the aerodynamic performance of the transition section is improved.
Description
Technical field
The present invention relates to aero engine technology field, particularly relate to a kind of engine transition section and the aeroengine of this engine transition section is set.
Background technique
Between turbine stage, casing is also called " changeover portion " (English can be translated into: TRANSITIONDUCT), and it is between high-pressure turbine, low-pressure turbine, and playing guide functions, is one of critical component of aeroengine.Changeover portion connects high-pressure turbine outlet, its outlet connects low-pressure turbine entrance (or claim: low-pressure turbine import), therefore, the aeroperformance of changeover portion affects the aeroperformance of low-pressure turbine strongly.Changeover portion is made up of support plate, upper end wall (or claim: outer end wall) and lower end wall (or claim: inner end wall), and the key of its pneumatic design is exactly the Design and optimization to wheel hub (i.e. inner end wall), casing (i.e. outer end wall) and support plate molded line.Usually, when the exit flow of upstream high turbine flows into changeover portion, the load-carrying construction of changeover portion inside can adopt outsourcing support plate to carry out water conservancy diversion to the air-flow flowing through the section of crossing.
The applicant finds: prior art at least exists following technical problem:
Due in prior art, when the load-carrying construction of transition intersegmental part adopts outsourcing support plate to carry out in the process of water conservancy diversion to the air-flow flowing through the section of crossing, the air-flow flowing into changeover portion easily produces and is separated near support plate trailing edge (English can be translated into: TRAILNGEDGE), this point of defection affects the aerodynamic characteristic of changeover portion itself, reduce the total pressure recovery performance of changeover portion, improve the pressure loss of changeover portion, development along with separation bubble directly can affect the flow quality of changeover portion outlet, also have impact on the aeroperformance of down stream low pressure turbine inlet.
Summary of the invention
One of them object of the present invention proposes a kind of engine transition section and arranges the aeroengine of this engine transition section, solves prior art and there is the poor technical problem of the aeroperformance of changeover portion.Many technique effects that optimal technical scheme in many technological schemes provided by the invention can produce refer to hereafter sets forth.
For achieving the above object, the invention provides following technological scheme:
The engine transition section that the embodiment of the present invention provides, the support plate comprising outer end wall, inner end wall and be arranged between described outer end wall and described inner end wall, wherein:
Described support plate is provided with the air-flow path running through described support plate, the air flow energy flow through from the pressure side of described support plate flows to the suction surface of described support plate through described air-flow path and drives the low energy fluid around described suction surface to flow to downstream.
In preferably or alternatively embodiment, described air-flow path is that air-flow gap is formed, and described support plate is divided into front supporting plate and rear supporting plate by described air-flow gap.
In preferably or alternatively embodiment, described front supporting plate and described rear supporting plate are blade-shaped separately, and described front supporting plate forms main wing, and described rear supporting plate forms wing flap, and described air-flow path is arranged on the trailing edge of described support plate.
In preferably or alternatively embodiment, the chord length of described wing flap is 5% ~ 45% of the chord length of described support plate.
In preferably or alternatively embodiment, the chord length of described wing flap is 10% ~ 30% of the chord length of described support plate.
In preferably or alternatively embodiment, the minimum range between point identical with slope on the pressure side of described main wing on the pressure side of described wing flap and the leading edge point of described wing flap is 25% ~ 35% of the length of described wing flap on described motor axial direction.
In preferably or alternatively embodiment, the trailing edge of described main wing is provided with water conservancy diversion plane, and described water conservancy diversion plane forms one of them sidewall in two relative sidewalls of described air-flow gap position.
In preferably or alternatively embodiment, the joint of the joint of the pressure side of described water conservancy diversion plane and described main wing and the suction surface of described water conservancy diversion plane and described main wing is provided with fillet or chamfering.
In preferably or alternatively embodiment, described flap surface is curve with the outer contour on the surface between the trailing edge of the described main wing point that slope is identical on the surface and the leading edge point of described wing flap, and described curve meets elliptic equation or parabolic equation: described elliptic equation is y
2+ ax2+bxy+cx=0, wherein: x is the abscissa value of each point on curve, y is the ordinate value of each point on curve, and a, b, c are for certainly setting coefficient.
In preferably or alternatively embodiment, described a, described b, described c value are separately-5 ~ 5.
In preferably or alternatively embodiment, described air-flow path is air-flow through hole.
In preferably or alternatively embodiment, described air-flow through hole be arranged on described support plate close to described outer end wall part, be arranged on described support plate close to the part of described inner end wall or be arranged on described support plate along described motor medium position in the radial direction.
The aeroengine that the embodiment of the present invention provides, comprises the engine transition section that the arbitrary technological scheme of the present invention provides, and described outer end wall is the internal surface of periphery casing, and described inner end wall is the outer surface of wheel hub.
In preferably or alternatively embodiment, described air-flow path is that air-flow gap is formed, described support plate is divided into front supporting plate and rear supporting plate by described air-flow gap, described aeroengine also comprises cooled gas input device, and the cooled gas delivery outlet of described cooled gas input device is towards the position of described air-flow path close to described outer end wall or described inner end wall.
Based on technique scheme, the embodiment of the present invention at least can produce following technique effect:
The air-flow path running through support plate is provided with due to the support plate in the engine transition section that the embodiment of the present invention provides (being preferably the trailing edge place of support plate), when upstream airflow (such as: high-pressure turbine exit flow) flows into changeover portion, due to the existence of air-flow path (gap be preferably between wing flap and main wing is formed), the air-flow of pressure side can flow to suction surface through air-flow path
Because the fluid flowing to suction surface has larger kinetic energy, it can drive the low energy fluid of suction surface to flow to downstream, avoid, at the trailing edge place of support plate, flow separation occurs, so improve the aeroperformance of changeover portion, solve prior art and there is the poor technical problem of the aeroperformance of changeover portion.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, and form a application's part, schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the schematic diagram of the support plate outer surface air-flow streamline of engine transition section in prior art;
The schematic diagram of the blade profile of the support plate of the engine transition section that Fig. 2 provides for the embodiment of the present invention;
The schematic diagram of the support plate outer surface air-flow streamline of the engine transition section that Fig. 3 provides for the embodiment of the present invention;
The enlarged diagram of the blade profile of the wing flap of the support plate of the engine transition section that Fig. 4 provides for the embodiment of the present invention;
The enlarged diagram of the blade profile of the support plate of the engine transition section that Fig. 5 provides for the embodiment of the present invention;
Fig. 6 is the enlarged diagram of the blade profile of wing flap shown in Fig. 5;
Reference character: 1, support plate; 11, main wing; 12, wing flap; 13, air-flow path; 121, water conservancy diversion plane; 14, fillet, E, point; F, point; G, point; H, point; I, point; J, point; K, point; L, point; M, point.
Embodiment
Content of the present invention and the distinctive points between the present invention and prior art can be understood below with reference to accompanying drawing Fig. 1 ~ Fig. 6 and word content.Hereafter by accompanying drawing and the mode enumerating embodiment more of the present invention, technological scheme of the present invention (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all one or more in the technical characteristics of plurality of optional or optional technological scheme, cannot exhaustive all alternative technical characteristicss of the present invention and alternative technological scheme in order to describe succinct to need in presents, also the mode of execution being not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: arbitrary technological means provided by the invention can be carried out replacing or two or more technological means or technical characteristics arbitrarily provided by the invention being carried out mutually combining and obtain new technological scheme.Any technical characteristics in the present embodiment and any technological scheme all do not limit the scope of the invention, protection scope of the present invention should comprise those skilled in the art do not pay creative work thinkable any alternate embodiments and those skilled in the art new technological scheme that two or more technological means or technical characteristics arbitrarily provided by the invention are carried out mutually combining and obtain.
Embodiments provide one can improve, suppress flow separation, the engine transition section that aeroperformance is ideal and arrange the aeroengine of this engine transition section.
Below in conjunction with the elaboration that Fig. 2 ~ Fig. 6 carries out specifically to technological scheme provided by the invention.
As shown in Fig. 2 ~ Fig. 6, the engine transition section that the embodiment of the present invention provides, comprises outer end wall, inner end wall and is arranged on the support plate as shown in Figure 21 between outer end wall and inner end wall, wherein:
On support plate 1, the trailing edge place of support plate 1 (be preferably) is provided with the air-flow path 13 running through support plate 1, and the air flow energy flow through from the pressure side of support plate 1 flows to the suction surface of support plate 1 through air-flow path 13 and drives the low energy fluid around suction surface to flow to downstream.
The air-flow path 13 running through support plate 1 is provided with due to support plate 1 in the engine transition section that the embodiment of the present invention provides (being preferably the trailing edge place of support plate 1), when upstream airflow (such as: high-pressure turbine exit flow) flows into changeover portion, due to the existence of air-flow path 13 (gap be preferably between wing flap 12 and main wing 11 is formed), the air-flow of pressure side can flow to suction surface through air-flow path 13, the fluid flowing to suction surface has larger kinetic energy, it can drive the low energy fluid of suction surface to flow to downstream, avoid, at the trailing edge place of support plate 1, flow separation occurs, so improve the aeroperformance of changeover portion.
As preferably or alternatively mode of execution, air-flow path 13 is that air-flow gap is formed, and support plate 1 is divided into front supporting plate and rear supporting plate by air-flow gap.Air-flow gap not only bore is comparatively large, and the aerodynamic loss caused the air-flow of process is less, and is convenient to arrange, and can save the material that support plate 1 expends.
As preferably or alternatively mode of execution, front supporting plate and rear supporting plate are blade-shaped separately, and front supporting plate forms main wing 11, and rear supporting plate forms wing flap 12.Air-flow path 13 is arranged on the trailing edge of support plate 1.The aerodynamic loss that the air-flow of blade-shaped structure to process causes is less, and better to the leading role of air-flow.
As preferably or alternatively mode of execution, the chord length of wing flap 12 is 5% ~ 45% of the chord length of support plate 1, and the chord length of wing flap 12 is preferably 10% ~ 30% of the chord length of support plate 1.Above-mentioned size value can guarantee that the position head piece of air-flow path 13 is close to the comparatively serious region of support plate 1 surrounding flow generation flow separation, the harm that can more effectively suppress flow separation to cause thus.
As preferably or alternatively mode of execution, the pressure side (side surface close to the influent stream mouth of air-flow path 13) of wing flap 12 is upper is 25% ~ 35% of the length of wing flap 12 on motor axial direction with pressure side (being preferably the trailing edge surface of the main wing 11) minimum range gone up between the identical point of slope and the leading edge point of wing flap 12 of main wing 11.Above-mentioned size value can guarantee that the width dimensions of air-flow path 13 is ideal, and then when guaranteeing that the flow losses that air-flow path 13 pairs of air-flows cause are less, effectively suppresses the harm that flow separation causes.
As preferably or alternatively mode of execution, the trailing edge of main wing 11 is provided with water conservancy diversion plane 121, and water conservancy diversion plane 121 forms one of them sidewall in two relative sidewalls of air-flow gap position.
Water conservancy diversion plane 121 is convenient to manufacture, processing, and the aerodynamic loss caused the air-flow flowed through is less.
As preferably or alternatively mode of execution, joint and the water conservancy diversion plane 121 of water conservancy diversion plane 121 and the pressure side of main wing 11 are provided with fillet 14 or chamfering with the joint of suction surface, are preferably fillet 14.
It is concentrated that fillet 14 or chamfering not only can avoid main wing 11 trailing edge arris place that stress occurs, and intensity is higher, but also can reduce it to the loss caused through air-flow.
As preferably or alternatively mode of execution, wing flap 12 is curve with the outer contour on the surface between the trailing edge point that slope is identical on the surface of main wing 11 and the leading edge point of wing flap 12 on the surface, and curve meets elliptic equation or parabolic equation: elliptic equation is y
2+ ax
2+ bxy+cx=0, wherein: x is the abscissa value of each point on curve, y is the ordinate value of each point on curve, and a, b, c are for certainly setting coefficient.The value of a, b, c can be-5 ~ 5, can certainly be other numerical value.Bent curvature of a curve can be changed by the value changing a, b, c, and then change the shape on wing flap 12 surface.
Above-mentioned shape can reduce the aerodynamic loss that wing flap 12 surface is caused the air-flow flow through as much as possible.
As shown in Figure 5 and Figure 6, in the present invention, the chord length of wing flap 12 can be 10% ~ 30% of support plate 1 chord length.The specific design method of wing flap 12 comprises wing flap 12 design method one and wing flap 12 design method two, specific as follows:
Wing flap 12 design method one:
Wing flap 12 is made up of many line segments and comprises:
Line segment one: some L is to trailing edge section; Point L apart from the distance of wing flap 12 trailing edge point M account for wing flap 12 on motor axial direction length 30% ~ 40%.L is identical with slope main wing 11 being put A for point.
By NACA series blade profile data determination main wing 11 streamline, main wing 11 streamline coordinate is known, can try to achieve A, C place coordinate, determines line segment AC by an A, some C (C is close as far as possible for some A, point), extend line segment AC pass through some L and extend, line segment CAL and elongation line thereof can be obtained.
Line segment two: some E is to leading edge segments; Point E apart from the distance of wing flap 12 leading edge point H account for wing flap 12 on motor axial direction length 25% ~ 35%; With line segment one in like manner, obtain the line segment DBE and elongation line thereof that are made up of a B, some D (B, D are close as far as possible for point), consider that processing technology etc. requires to determine trailing edge diameter (such as 4mm), obtain the circle being simultaneously inscribed within line segment BE, AL, then the position of wing flap 12 trailing edge point can be determined.
Curve three: some E is to some H to putting L, and this part line segment is at least made up of two-part: curve EH, curve HL, and its mid point H is wing flap 12 leading edge point.For improving curve precision, this curve can artificially increase line segment number.This case is only for two sections, and curve EH, curve HL respectively available elliptic equation realize: y
2+ ax
2+ bxy+cx=0) (in formula, a, b, c are the coefficient that can certainly establish, by these coefficients can controlling curve EH, curve HL amount of curvature; Except elliptic equation, parabolic equation also can realize the configuration design of curve EH, curve HL), this equation meets the infinitely-great condition of head slope automatically.Such as: curve EH can choose elliptic equation:
Curve HL can choose elliptic equation:
Wing flap 12 design method two:
Use blade shape construction software, according to flow field streamline details, by adjustment wing flap 12 molded line, carry out Flow Field Calculation and analysis, iteration carries out above-mentioned steps until flow field is without obvious separation, in flow field without under separation case, determines wing flap 12 profile satisfied condition.
In the embodiment of the present invention, the specific design of main wing 11 trailing edge has the following two kinds method:
Main wing 11 trailing edge design method one: main wing 11 trailing edge also realizes by application elliptic equation.
Main wing 11 trailing edge design method two: by directly connecting main wing 11 afterbody top airfoil, lower aerofoil two end point A, some B, then circle realization is led to upper and lower two interior angles of aerofoil.
Embodiment 2:
The present embodiment is substantially the same manner as Example 1, and its difference is: in the present embodiment, air-flow path 13 is air-flow through hole.The support plate 1 arranging air-flow through hole has is convenient to processing, manufacture, transport, and the advantage that structural strength is higher.
As preferably or alternatively mode of execution, air-flow through hole be arranged on support plate 1 close to outer end wall part, be arranged on support plate 1 close to the part of inner end wall or be arranged on support plate 1 along motor medium position in the radial direction.Above setting position all can play the effect suppressing support plate 1 ambient dynamic to be separated in various degree.Certainly, air-flow path 13 also can be the combination in air-flow through hole and air-flow gap, and such as: air-flow path 13 part is air-flow through hole, part is air-flow gap.
As shown in Fig. 2 ~ Fig. 6, the aeroengine that the embodiment of the present invention provides, comprises the engine transition section that the arbitrary technological scheme of the present invention provides, and outer end wall is the internal surface of periphery casing, and inner end wall is the outer surface of wheel hub.The harm that the engine transition section that aeroengine is suitable for adopting the arbitrary technological scheme of the present invention to provide suppresses flow separation to produce to improve it, improves its aeroperformance.
As preferably or alternatively mode of execution, air-flow path 13 is the formation of air-flow gap, support plate 1 is divided into front supporting plate and rear supporting plate by air-flow gap, aeroengine also comprises cooled gas input device (or claim: air inlet system), and the cooled gas delivery outlet of cooled gas input device is towards the position of air-flow path 13 close to outer end wall or inner end wall.Air inlet system can improve the cooling effect of changeover portion, and then extends working life and the Security of transition section structure.
The technological scheme that the embodiment of the present invention 1 provides and prior art laboratory data contrast:
| Changeover portion | Total pressure recovery coefficient % | Total pressure loss coefficient % |
| Prior art | 99.326 | 8.273 |
| The present invention | 99.426 | 6.974 |
| Improvement amplitude | +0.1 | -1.299 |
Arbitrary technological scheme disclosed in the invention described above unless otherwise stated, if the number range of it discloses, so disclosed number range is preferred number range, anyly it should be appreciated by those skilled in the art: preferred number range is only the numerical value that in many enforceable numerical value, technique effect is obvious or representative.Because numerical value is more, cannot be exhaustive, so the present invention just discloses component values to illustrate technological scheme of the present invention, and the above-mentioned numerical value enumerated should not form the restriction to the invention protection domain.
If employ the word such as " first ", " second " herein to limit component, those skilled in the art should know: the use of " first ", " second " is only used to be convenient to describe carry out difference as not having outside Stated otherwise to component, the implication that above-mentioned word is not special.
Simultaneously, if the invention described above discloses or relate to component or the structural member of connection fastened to each other, so, unless otherwise stated, be fixedly connected with and can be understood as: can releasably be fixedly connected with (such as using bolt or screw to connect), also can be understood as: to be non-removablely fixedly connected with (such as rivet, weld), certainly, connection fastened to each other also can be replaced by integral type structure (such as use casting technique is integrally formed create) (obviously cannot adopt except integrally formed technique).
In addition, apply in arbitrary technological scheme disclosed in the invention described above for represent position relationship or shape term unless otherwise stated its implication comprise approximate with it, similar or close state or shape.Arbitrary parts provided by the invention both can be assembled by multiple independent constituent element, and also can be one of the forming manufacture technics separate part out.
Finally should be noted that: above embodiment is only in order to illustrate that technological scheme of the present invention is not intended to limit; Although with reference to preferred embodiment to invention has been detailed description, those of ordinary skill in the field are to be understood that: still can modify to the specific embodiment of the present invention or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solution of the present invention, it all should be encompassed in the middle of the technological scheme scope of request of the present invention protection.
Claims (14)
1. an engine transition section, is characterized in that, the support plate comprising outer end wall, inner end wall and be arranged between described outer end wall and described inner end wall, wherein:
Described support plate is provided with the air-flow path running through described support plate, the air flow energy flow through from the pressure side of described support plate flows to the suction surface of described support plate through described air-flow path and drives the low energy fluid around described suction surface to flow to downstream.
2. engine transition section according to claim 1, is characterized in that, described air-flow path is that air-flow gap is formed, and described support plate is divided into front supporting plate and rear supporting plate by described air-flow gap.
3. engine transition section according to claim 2, is characterized in that, described front supporting plate and described rear supporting plate are blade-shaped separately, and described front supporting plate forms main wing, and described rear supporting plate forms wing flap, and described air-flow path is arranged on the trailing edge of described support plate.
4. engine transition section according to claim 3, is characterized in that, the chord length of described wing flap is 5% ~ 45% of the chord length of described support plate.
5. engine transition section according to claim 3, is characterized in that, the chord length of described wing flap is 10% ~ 30% of the chord length of described support plate.
6. engine transition section according to claim 3, it is characterized in that, the minimum range between point identical with slope on the pressure side of described main wing on the pressure side of described wing flap and the leading edge point of described wing flap is 25% ~ 35% of the length of described wing flap on described motor axial direction.
7. engine transition section according to claim 3, is characterized in that, the trailing edge of described main wing is provided with water conservancy diversion plane, and described water conservancy diversion plane forms one of them sidewall in two relative sidewalls of described air-flow gap position.
8. engine transition section according to claim 7, is characterized in that, the joint of the joint of the pressure side of described water conservancy diversion plane and described main wing and the suction surface of described water conservancy diversion plane and described main wing is provided with fillet or chamfering.
9. engine transition section according to claim 3, it is characterized in that, described flap surface is curve with the outer contour on the surface between the trailing edge of the described main wing point that slope is identical on the surface and the leading edge point of described wing flap, and described curve meets elliptic equation or parabolic equation: described elliptic equation is y
2+ ax
2+ bxy+cx=0, wherein: x is the abscissa value of each point on curve, y is the ordinate value of each point on curve, and a, b, c are for certainly setting coefficient.
10. engine transition section according to claim 9, is characterized in that, described a, described b, described c value are separately-5 ~ 5.
11. engine transition sections according to claim 1, is characterized in that, described air-flow path is air-flow through hole.
12. engine transition sections according to claim 11, it is characterized in that, described air-flow through hole be arranged on described support plate close to described outer end wall part, be arranged on described support plate close to the part of described inner end wall or be arranged on described support plate along described motor medium position in the radial direction.
13. 1 kinds of aeroengines, is characterized in that, comprise the arbitrary described engine transition section of claim 1-12, described outer end wall is the internal surface of periphery casing, and described inner end wall is the outer surface of wheel hub.
14. aeroengines according to claim 13, it is characterized in that, described air-flow path is that air-flow gap is formed, described support plate is divided into front supporting plate and rear supporting plate by described air-flow gap, described aeroengine also comprises cooled gas input device, and the cooled gas delivery outlet of described cooled gas input device is towards the position of described air-flow path close to described outer end wall or described inner end wall.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410499761.6A CN105443162B (en) | 2014-09-26 | 2014-09-26 | Engine transition section and aero-engine |
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|---|---|---|---|
| CN201410499761.6A CN105443162B (en) | 2014-09-26 | 2014-09-26 | Engine transition section and aero-engine |
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| CN105443162A true CN105443162A (en) | 2016-03-30 |
| CN105443162B CN105443162B (en) | 2017-04-19 |
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| EP1112928A2 (en) * | 1999-12-31 | 2001-07-04 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Airfoil with performance enhancing trailing edge |
| US20030059291A1 (en) * | 2001-09-27 | 2003-03-27 | Koshoffer John Michael | Method and apparatus for reducing distortion losses induced to gas turbine engine airflow |
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| EP1947294A2 (en) * | 2007-01-17 | 2008-07-23 | United Technologies Corporation | Airfoil with device against boundary layer separation |
| CN101779003A (en) * | 2008-01-21 | 2010-07-14 | 三菱重工业株式会社 | Turbine blade-cascade end wall |
| CN202202902U (en) * | 2011-06-30 | 2012-04-25 | 中航商用航空发动机有限责任公司 | Intermediate case for aeroengine |
| US20130330180A1 (en) * | 2012-06-01 | 2013-12-12 | MTU Aero Engines AG | Passage channel for a turbomachine and turbomachine |
| CN203515810U (en) * | 2013-09-09 | 2014-04-02 | 中国科学院工程热物理研究所 | Transition section structure of high-low-pressure turbine |
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2014
- 2014-09-26 CN CN201410499761.6A patent/CN105443162B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2914241A (en) * | 1955-11-30 | 1959-11-24 | Gen Electric | Means for adjusting the flow characteristics of fluid flow machines |
| EP1112928A2 (en) * | 1999-12-31 | 2001-07-04 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Airfoil with performance enhancing trailing edge |
| US20030059291A1 (en) * | 2001-09-27 | 2003-03-27 | Koshoffer John Michael | Method and apparatus for reducing distortion losses induced to gas turbine engine airflow |
| CN1955441A (en) * | 2005-10-25 | 2007-05-02 | 联合工艺公司 | Variable geometry inlet guide vane |
| EP1947294A2 (en) * | 2007-01-17 | 2008-07-23 | United Technologies Corporation | Airfoil with device against boundary layer separation |
| CN101779003A (en) * | 2008-01-21 | 2010-07-14 | 三菱重工业株式会社 | Turbine blade-cascade end wall |
| CN202202902U (en) * | 2011-06-30 | 2012-04-25 | 中航商用航空发动机有限责任公司 | Intermediate case for aeroengine |
| US20130330180A1 (en) * | 2012-06-01 | 2013-12-12 | MTU Aero Engines AG | Passage channel for a turbomachine and turbomachine |
| CN203515810U (en) * | 2013-09-09 | 2014-04-02 | 中国科学院工程热物理研究所 | Transition section structure of high-low-pressure turbine |
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| Publication number | Publication date |
|---|---|
| CN105443162B (en) | 2017-04-19 |
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