CN114542287A - Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface - Google Patents

Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface Download PDF

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Publication number
CN114542287A
CN114542287A CN202210146209.3A CN202210146209A CN114542287A CN 114542287 A CN114542287 A CN 114542287A CN 202210146209 A CN202210146209 A CN 202210146209A CN 114542287 A CN114542287 A CN 114542287A
Authority
CN
China
Prior art keywords
casing
air
shovel
flow
guide
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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.)
Pending
Application number
CN202210146209.3A
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Chinese (zh)
Inventor
麻丽春
王海
方浩
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AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202210146209.3A priority Critical patent/CN114542287A/en
Publication of CN114542287A publication Critical patent/CN114542287A/en
Pending legal-status Critical Current

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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
    • 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
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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

Abstract

The application provides a reduce bleed structure of quick-witted casket wall circumference temperature inhomogeneity includes: the inner-layer casing, the outer-layer casing and the casing rear baffle are all annular, and the inner-layer casing, the outer-layer casing and the casing rear baffle are encircled together to form a double-layer casing structure with a cooling cavity; the outer-layer casing is provided with a plurality of air inlet holes and air outlet holes which are arranged at intervals, and the air-entraining pipe is arranged on the outer side of the outer-layer casing corresponding to the air-entraining holes; the guide shovel is provided with an assembly surface matched with the outer-layer casing, an opening is formed in the assembly surface, a lateral guide surface and a bottom guide surface extend to one side of the inner-layer casing along the edge of the opening on the assembly surface, and a preset angle is formed between the bottom guide surface and the assembly surface; the cooling gas flowing in from the flow guide pipe obliquely flows along the same direction in the circumferential direction along the air inlet hole and the flow guide shovel in the cooling cavity of the double-layer casing structure and flows out from the air outlet hole.

Description

Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a bleed structure for reducing circumferential temperature nonuniformity of a casing wall surface.
Background
The casing is used as an important component of a force bearing system of the aircraft engine, the wall surface of a gas channel is directly or indirectly formed by some casings, and the working reliability of the engine is directly influenced by the deformation of the casings caused by stress and heating. In the case bleed air flow path, reasonable selection and design of bleed air positions and structures can ensure that the cooling of hot end parts meets design requirements in a full-envelope range.
The conventional casing air-entraining structure of an engine (or a test piece) is mainly used for conveying main channel air flow (or rack air flow) to a required position through an air-entraining pipeline to realize the function of an air system, and is limited by a space structure and air-entraining requirements. Although the air-entraining structure can reduce the wall temperature of the casing, the circumferential temperature of the wall surface of the casing is easy to be uneven, so that the thermal deformation of the casing is inconsistent, and the working reliability of the casing is influenced.
Therefore, under the structural constraint, how to ensure the circumferential temperature uniformity of the wall surface of the casing is a problem to be solved urgently.
Disclosure of Invention
The purpose of the present application is to provide a bleed air structure that reduces circumferential temperature non-uniformity in the casing wall surface to solve or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: a bleed air structure for reducing circumferential temperature non-uniformity in a wall of a casing, the bleed air structure comprising: inlayer machine casket, outer machine casket, machine casket backplate, bleed pipe and water conservancy diversion shovel, wherein:
the inner-layer casing, the outer-layer casing and the casing rear baffle are all annular, and the inner-layer casing, the outer-layer casing and the casing rear baffle are encircled together to form a double-layer casing structure with a cooling cavity;
the outer-layer casing is provided with a plurality of air inlet holes and air outlet holes which are arranged at intervals, and the air-entraining pipe is arranged on the outer side of the outer-layer casing at the corresponding position of the air-entraining hole; and
the flow guide shovel is arranged on the inner side of the outer-layer casing at a position corresponding to the air guide hole, and is provided with an assembling surface matched with the outer-layer casing, an opening is formed in the assembling surface, and a lateral flow guide surface and a bottom flow guide surface extend to one side of the inner-layer casing along the edge of the opening on the assembling surface, wherein a preset angle is formed between the bottom flow guide surface and the assembling surface;
the cooling gas flowing in from the guide pipe obliquely flows in the same direction along the circumferential direction of the cooling cavity of the double-layer casing structure along the air inlet hole and the guide shovel and flows out from the air outlet hole.
Furthermore, the assembly surface of the flow guide shovel is arc-shaped, and the radian of the assembly surface is matched with the radian of the inner surface of the outer casing.
Furthermore, one side of the opening is an arc, and the other side of the opening is a straight line which is tangent to the arc and gradually expands in distance to form an open structure.
Furthermore, the lateral flow guide surface of the flow guide shovel and the side edge of the flow guide shovel form an acute included angle.
Furthermore, the distance between the bottom diversion surface of the diversion shovel and the outer casing is gradually increased from one side of the arc of the opening to the other side.
Furthermore, a plurality of mounting holes with thread structures are formed in the assembling surface of the flow guide shovel, and the flow guide shovel is connected with the outer casing through a connecting piece.
Furthermore, the mounting holes include three, the mounting hole of one of the mounting holes is located on the central line of the flow guide shovel, and the connecting line of the other two mounting holes is perpendicular to the central line.
Furthermore, the circumferential arrangement directions of the plurality of flow guide shovels on the inner side of the outer-layer casing are the same.
Set up the water conservancy diversion structure through the bleed air kneck of outer skin machine casket in this application, with the flow path direction that changes the interior air conditioning of double-deck machine casket of entering, let the perpendicular efflux originally become the slant and flow, weaken the entry and strike, thereby reduce spray tube machine casket inner layer structure circumference temperature inhomogeneity, on the basis that does not change former engine or test piece structure, newly-increased water conservancy diversion structure can reduce the unevenness of machine casket wall circumference temperature, structural change is little, processing is convenient, easily assemble, can be applied to in the double-deck machine casket structure of multiple model engine or test piece.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Figure 1 is a schematic view of the bleed air structure composition of the present application.
Fig. 2 is a schematic view of a diversion shovel in the present application.
Fig. 3 is a top view of the present disclosure of a diversion shovel.
Fig. 4 is a cross-sectional view of the guide shovel in fig. 3.
Fig. 5 is a schematic view of the bleed air structure assembly relationship in the present application.
Fig. 6 is a schematic view of the distribution of the connection parts for assembling the bleed air structure and the casing according to the present application.
Figure 7 is a schematic view of the bleed air structure and casing assembly process of the present application.
FIG. 8 is a schematic view of the flow direction of cooling air in a casing structure without a flow guiding shovel.
FIG. 9 is a schematic view of the cooling air flow direction of the casing structure with a flow guiding shovel.
FIG. 10 is a graph of the simulation results of the casing wall temperature without a flow-guiding shovel.
FIG. 11 is a diagram of simulation results of casing wall temperature with a flow guiding structure.
FIG. 12 is a schematic diagram comparing the wall temperature of the casing.
Reference numerals
1-inner layer casing
2-outer casing
3-casing tailgate
4-air-entraining pipe
5-diversion shovel
51-mounting surface
52-mounting hole
53-side guide surface
54-bottom flow guide surface
55-opening
551-center line
56-end of flow guide surface
6-screw
7-stud
8-nut
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
Fig. 1 is a schematic view of a bleed air structure capable of reducing circumferential temperature unevenness of a casing wall surface, which is provided by the present application, and the bleed air structure mainly includes: the structure comprises an inner-layer casing 1, an outer-layer casing 2, a casing rear baffle 3, a gas guide pipe 4 and a flow guide shovel 5, wherein the inner-layer casing 1, the outer-layer casing 2 and the casing rear baffle 3 are all annular, and the three jointly surround to form a double-layer casing structure with a cooling cavity 11. The inner casing 1 is in direct contact with the engine gas and needs to be cooled efficiently. The double-layer casing structure adopts a bleed air cooling mode, a plurality of air inlet holes and air outlet holes which are arranged at intervals are formed in the outer casing 2, and the bleed air pipe 4 is installed on the outer casing 2 at the position of the bleed air holes and used for introducing external cooling air into the cooling cavity 11 through the bleed air pipe 4, so that the inner casing 1 is cooled. The flow guide shovel 5 is arranged on the inner side of the air inlet of the outer-layer casing 2, and the uniformity of air flow in the cooling cavity 11 is improved through the flow guide shovel 5, so that the height difference of the wall surface of the inner-layer casing 1 is reduced.
As shown in fig. 2, the guide shovel 5 has a substantially dustpan shape, and has a fitting surface 51 at an upper portion thereof for fitting to the outer casing 2. Preferably, the mounting surface 51 is an arc-shaped surface having the same curvature as the inner curvature of the outer casing 2.
An opening 55 is formed in the mounting surface 51, and one end of the opening 55 is formed in an arc shape, and the other end of the opening 55 has an open configuration which is tangent to the arc and gradually expands. A plurality of mounting holes 52 are provided at the edge of the opening 55 of the mounting surface 51, and the spatula 5 and the outer casing 2 can be connected by a connecting member and the mounting holes 52.
A lateral guide surface 53 and a bottom guide surface 54 extend inward (toward the inner casing) along an inner edge of the opening 55, and the height of the lateral guide surface 53 gradually increases or increases from the arc end of the opening 55 toward the open end, so that the distance between the bottom guide surface 54 and the mounting surface 51 gradually increases from the arc end of the opening 55 toward the open end. Preferably, two of the lateral guiding surfaces 53 are non-parallel to each other, the two lateral guiding surfaces 53 are perpendicular to the mounting surface 51, and a substantially rectangular exhaust port is formed at the guiding surface end 56 of the guiding shovel 5, so that the opening 55 is expanded from the air inlet end to the air outlet end.
As shown in fig. 3 and 4, which are typical size diagrams of the guide shovel 5, the opening 55 of the guide shovel 5 has a center line 551, the distances between the center line 551 of the guide shovel 5 and the two axial side wall surfaces of the casing are L1 and L2, respectively, the included angles between the lateral guide surfaces 53 of the guide shovel 5 and the two side edges thereof are α 1 and α 2 (i.e., the axial expansion angle of the guide shovel 5), the angle between the mounting surface 51 and the bottom guide surface 54 of the guide shovel 5 is β, the diameter of the circular arc portion of the opening 55 in the mounting surface 51 is D, the radial height H of the air outlet position at the end of the bottom guide surface 54 (i.e., the distance between the end of the bottom guide surface 54 and the outer casing 2, and the distance increases from left to right), and a chamfer r is provided between the bottom guide surface 54 and the mounting surface 51 and/or the lateral guide surfaces 53. It should be noted that the above typical dimensions are not fixed values, and can be flexibly adjusted according to a specific casing.
As shown in fig. 5, which is an assembly structure diagram of the flow guiding shovel 5, the flow guiding shovel 5 is located between the outer casing 2 and the inner casing 1, a smooth through hole is formed in a position where the outer casing 2 is matched with the mounting hole 52, two ends of the stud 7 are of a threaded structure, the middle part of the stud is a non-threaded section matched with the smooth through hole, a threaded structure is arranged in the mounting hole 52 of the flow guiding shovel 5, and the three parts are installed by matching the lower end of the stud 7 with the mounting hole 52, passing the middle part of the stud through the outer casing 2 and the guide pipe 4, and matching the upper end of the stud with the nut 8.
As shown in fig. 6, which is a top view of an assembly structure of the air guide shovel 5, there are three mounting holes 52 of the air guide shovel 5, eight holes are circumferentially arranged on a mounting edge of the air guide pipe 4, the air guide pipe 4 is connected with the outer casing 2 through five screws 6, the air guide shovel 5, the outer casing 2 and the air guide pipe 4 are connected through three studs 7 and nuts 8 at corresponding positions, the positions of the three studs are distributed as shown in fig. 7, one mounting hole 52 is located on a center line 551, and the connecting line of the other two mounting holes 52 is perpendicular to the center line 551.
In an engine or a test piece, the assembly surface of the flow guide shovel 5 and the surface of the air guide hole in the outer casing 2 are assembled, after air flow flowing in from the air guide pipe passes through the flow guide shovel 5, the original vertical jet flow is changed into oblique flow, the inlet impact is weakened, the coverage area of the oblique flow on the casing wall surface is larger, the cooling area is increased, the temperature difference between the high temperature and the low temperature of the casing wall surface can be effectively reduced, and the circumferential temperature unevenness of the wall surface is weakened.
As shown in fig. 8 and 9, the test piece casing is a bleed air structure without a diversion shovel and with a diversion shovel, which has 3 air inlet holes and 3 air outlet holes in the circumferential direction, respectively, and the air inlet holes and the air outlet holes are arranged at intervals, wherein in the bleed air structure with the diversion shovel 5 shown in fig. 9, the diversion shovel 5 is arranged at each air inlet hole, and the diversion directions of the diversion shovel 5 are the same, so that the flow direction of the cooling air inside the casing rotates clockwise.
As shown in fig. 10 and fig. 11, which are the results of the temperature of the inner wall surface of the casing in the air-entraining structure without the flow-guiding shovel and the air-entraining structure with the flow-guiding shovel, respectively, the air flow in the air-entraining structure without the flow-guiding shovel is equivalent to vertical impact, the flow direction is in the form of "inlet split flow and outlet confluence", the inner wall surface of the casing has a low temperature region at the inlet position, a high temperature region at the outlet position, and the circumferential temperature difference is large; and the air current is equivalent to oblique impact in the air-entraining structure with the flow-guiding shovel, the air current freely develops along the same direction in the circumferential direction, the oblique movement impact distance is long, the position of wall surface movement is far, and the temperature of the inner wall surface of the casing is uniform.
As shown in fig. 12, which is a casing wall temperature distribution curve in the air-entraining structure without a flow-guiding shovel and the air-entraining structure with a flow-guiding shovel, compared with the air-entraining structure without a flow-guiding shovel, the casing wall temperature difference (i.e., the height difference between the peak value and the peak valley) under the air-entraining structure with a flow-guiding shovel can be reduced by 50%.
Set up the water conservancy diversion structure through the bleed air kneck of outer skin machine casket in this application, with the flow path direction that changes the interior air conditioning of double-deck machine casket of entering, let the perpendicular efflux originally become the slant and flow, weaken the entry and strike, thereby reduce spray tube machine casket inner layer structure circumference temperature inhomogeneity, on the basis that does not change former engine or test piece structure, newly-increased water conservancy diversion structure can reduce the unevenness of machine casket wall circumference temperature, structural change is little, processing is convenient, easily assemble, can be applied to in the double-deck machine casket structure of multiple model engine or test piece.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (8)

1. A bleed air structure for reducing circumferential temperature non-uniformity of a wall surface of a casing, the bleed air structure comprising: inlayer machine casket (1), outer machine casket (2), quick-witted casket backplate (3), bleed pipe (4) and water conservancy diversion shovel (5), wherein:
the inner-layer casing (1), the outer-layer casing (2) and the casing rear baffle (3) are all annular, and the inner-layer casing (1), the outer-layer casing (2) and the casing rear baffle (3) are enclosed together to form a double-layer casing structure with a cooling cavity (11);
the outer-layer casing (2) is provided with a plurality of air inlet holes and air outlet holes which are arranged at intervals, and the air-entraining pipe (4) is arranged on the outer side of the outer-layer casing (2) at the position corresponding to the air-entraining holes; and
the flow guide shovel (5) is installed on the inner side of the outer casing (2) at the position corresponding to the air guide hole, the flow guide shovel (5) is provided with a mounting surface (51) used for being matched with the outer casing (2), an opening (55) is formed in the mounting surface (51), a lateral flow guide surface (53) and a bottom flow guide surface (54) extend to one side of the inner casing (1) along the edge of the opening (55) on the mounting surface (51), and a preset angle is formed between the bottom flow guide surface (54) and the mounting surface (51);
the cooling gas flowing in from the flow guide pipe (4) obliquely flows along the same direction in the circumferential direction of a cooling cavity (11) of the double-layer casing structure along the air inlet hole and the flow guide shovel (5) and flows out from the air outlet hole.
2. The bleed air structure for reducing circumferential temperature unevenness of the casing wall surface according to claim 1, wherein the mounting surface (51) of the air guide scoop (5) is arc-shaped, and the radian of the mounting surface is adapted to the radian of the inner surface of the outer casing (2).
3. The bleed air structure for reducing circumferential temperature unevenness of a casing wall surface according to claim 1, wherein the opening (55) is formed in an open structure by a circular arc on one side and a straight line which is tangent to the circular arc and gradually increases in distance on the other side.
4. The air-entraining structure for reducing the circumferential temperature nonuniformity of the wall surface of the casing according to claim 3, wherein the lateral flow-guiding surface (53) of the flow-guiding shovel (5) forms an acute included angle with the side edge of the flow-guiding shovel.
5. The bleed air structure for reducing the circumferential temperature unevenness of the wall surface of the casing as claimed in claim 3, wherein the distance between the bottom guide surface (54) of the guide shovel (5) and the outer casing (2) is gradually increased from one side of the arc of the opening to the other side.
6. The air-entraining structure for reducing the circumferential temperature nonuniformity of the wall surface of the casing according to any one of claims 2 to 5, wherein a plurality of mounting holes (52) with a threaded structure are formed in a mounting surface (51) of the flow-guiding shovel (5), and the flow-guiding shovel (5) is connected with the outer casing (2) through a connecting piece.
7. The bleed air structure for reducing circumferential temperature unevenness of the wall surface of the casing according to claim 6, wherein the number of the mounting holes (53) is three, one of the mounting holes (53) is located on a central line of the guide shovel (5), and a connecting line of the other two mounting holes (53) is perpendicular to the central line.
8. The bleed air structure for reducing circumferential temperature unevenness of the casing wall surface according to claim 1, wherein the plurality of flow guide shovels (5) are arranged in the same circumferential direction inside the outer casing (2).
CN202210146209.3A 2022-02-17 2022-02-17 Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface Pending CN114542287A (en)

Priority Applications (1)

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CN202210146209.3A CN114542287A (en) 2022-02-17 2022-02-17 Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface

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Application Number Priority Date Filing Date Title
CN202210146209.3A CN114542287A (en) 2022-02-17 2022-02-17 Air entraining structure for reducing circumferential temperature nonuniformity of casing wall surface

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Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5980201A (en) * 1996-06-27 1999-11-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device for blowing gases for regulating clearances in a gas turbine engine
US6584766B1 (en) * 2000-03-24 2003-07-01 General Electric Co. Methods and apparatus for minimizing thermal stresses in a centerbody
CN1704573A (en) * 2004-06-01 2005-12-07 通用电气公司 Method and apparatus for cooling combustor liner and transition piece of a gas turbine
US20130149107A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
US20130149120A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine engine with outer case ambient external cooling system
US20150330238A1 (en) * 2014-05-14 2015-11-19 Rolls-Royce Plc Distributor device for cooling air within an engine
US20160069273A1 (en) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air
CN112228168A (en) * 2020-10-21 2021-01-15 中国航发沈阳发动机研究所 Gas collection drainage structure for cooling inner cavity of stator blade
CN213298058U (en) * 2020-09-17 2021-05-28 中国航发商用航空发动机有限责任公司 Turbine blade cooling system and aircraft engine
CN213478401U (en) * 2020-09-17 2021-06-18 中国航发商用航空发动机有限责任公司 Turbine blade cooling system and aircraft engine
US20210246832A1 (en) * 2020-02-07 2021-08-12 Raytheon Technologies Corporation Flow diverter for mid-turbine frame cooling air delivery

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5980201A (en) * 1996-06-27 1999-11-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device for blowing gases for regulating clearances in a gas turbine engine
US6584766B1 (en) * 2000-03-24 2003-07-01 General Electric Co. Methods and apparatus for minimizing thermal stresses in a centerbody
CN1704573A (en) * 2004-06-01 2005-12-07 通用电气公司 Method and apparatus for cooling combustor liner and transition piece of a gas turbine
US20130149107A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
US20130149120A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine engine with outer case ambient external cooling system
US20150330238A1 (en) * 2014-05-14 2015-11-19 Rolls-Royce Plc Distributor device for cooling air within an engine
US20160069273A1 (en) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air
US20210246832A1 (en) * 2020-02-07 2021-08-12 Raytheon Technologies Corporation Flow diverter for mid-turbine frame cooling air delivery
CN213298058U (en) * 2020-09-17 2021-05-28 中国航发商用航空发动机有限责任公司 Turbine blade cooling system and aircraft engine
CN213478401U (en) * 2020-09-17 2021-06-18 中国航发商用航空发动机有限责任公司 Turbine blade cooling system and aircraft engine
CN112228168A (en) * 2020-10-21 2021-01-15 中国航发沈阳发动机研究所 Gas collection drainage structure for cooling inner cavity of stator blade

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