CN112211683B - Thermal shield for turbine rear casing - Google Patents
Thermal shield for turbine rear casing Download PDFInfo
- Publication number
- CN112211683B CN112211683B CN202011133235.XA CN202011133235A CN112211683B CN 112211683 B CN112211683 B CN 112211683B CN 202011133235 A CN202011133235 A CN 202011133235A CN 112211683 B CN112211683 B CN 112211683B
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- Prior art keywords
- heat shield
- frame
- basin
- shield blade
- supporting framework
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
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- 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
- F02C7/24—Heat or noise insulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
Abstract
The application belongs to the field of aero-engine and gas turbine design, and particularly relates to a turbine rear casing heat shield. The method comprises the following steps: force bearing frame, supporting framework and heat shield. The bearing frame comprises an outer end frame, an inner end frame and a bearing support plate arranged between the outer end frame and the inner end frame; the supporting framework is positioned behind the bearing support plate, one end of the supporting framework is connected with the outer end frame of the bearing frame, and the other end of the supporting framework is connected with the inner end frame of the bearing frame; the thermal shield is streamline, the thermal shield is sleeved on the outer side of the bearing support plate, the thermal shield comprises a thermal shield blade back and a thermal shield blade basin, the first end of the thermal shield blade back is connected with the first end of the thermal shield blade basin, and the second end of the thermal shield blade back and the second end of the thermal shield blade basin are connected with the support framework. The application can effectively reduce the aerodynamic loss of the fuel gas runner, thereby reducing the fuel consumption rate and ensuring that the use economy of the engine is better.
Description
Technical Field
The application belongs to the field of aero-engine and gas turbine design, and particularly relates to a turbine rear casing heat shield.
Background
In the turbine rear casing of modern aeroengines and gas turbines, a heat shield is generally adopted to surround the outer periphery of a bearing support plate of a bearing frame of the turbine rear casing. The bearing support plate is isolated from the fuel gas by the heat shield, so that the surface temperature of the bearing support plate is reduced, and the service life is prolonged.
In the prior art, the modeling of the heat shield is generally simply designed into a runway type, and the modeling can generate a blocking effect on a fuel flow channel, thereby causing the problems of large pneumatic loss and high fuel consumption rate.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a turbine aft case heat shield to address at least one problem with the prior art.
The technical scheme of the application is as follows:
an aft turbine case heat shield comprising:
the bearing frame comprises an outer end frame, an inner end frame and a bearing support plate arranged between the outer end frame and the inner end frame;
the supporting framework is positioned behind the bearing support plate, one end of the supporting framework is connected with the outer end frame of the bearing frame, and the other end of the supporting framework is connected with the inner end frame of the bearing frame;
the thermal shield is streamlined and sleeved outside the bearing support plate and comprises a thermal shield blade back and a thermal shield blade basin, the first end of the thermal shield blade back is connected with the first end of the thermal shield blade basin, and the second end of the thermal shield blade back and the second end of the thermal shield blade basin are connected with the support framework.
Optionally, the outrigger has a parallelogram in cross section.
Optionally, the supporting framework is connected with the outer end frame and the inner end frame of the bearing frame through bolts matched with the first nuts.
Optionally, the wall thickness of each of the heat shield blade back and the heat shield blade basin is 1 mm-2.5 mm.
Optionally, a countersunk bolt hole has been seted up to the first end of heat exchanger leaf back, the first end of heat exchanger leaf basin is provided with nut assembly, nut assembly includes second nut, locking plate and rivet, the second nut passes through the locking plate cooperation the fix with rivet is in the first end of heat exchanger leaf basin will through countersunk screw the first end of heat exchanger leaf back with heat exchanger leaf basin separates the nut assembly and connects.
Optionally, the first end of the heat shield blade back is uniformly provided with 5 countersunk bolt holes along the radial direction, and the first end of the heat shield blade basin is uniformly provided with 5 sets of nut assemblies along the radial direction.
Optionally, countersunk bolt holes are respectively formed at the second end of the heat shield blade back and the second end of the heat shield blade basin, a nut component is arranged on the support framework, and the second end of the heat shield blade back and the second end of the heat shield blade basin are connected with the nut component of the support framework through countersunk screws.
Optionally, mutually spaced recesses are respectively formed in two sides of the supporting framework, the nut assembly is installed in the recess, the second end of the thermal shield blade back is connected with the nut assembly in the recess on one side of the supporting framework through a countersunk screw, and the second end of the thermal shield blade basin is connected with the nut assembly in the recess on the other side of the supporting framework through a countersunk screw.
The invention has at least the following beneficial technical effects:
the utility model provides a turbine rear casing separates heat exchanger can reduce load extension board surface temperature, and then improves life, can effectively reduce the aerodynamic loss of gas runner to reduce the oil consumption rate, make the engine use economic nature better.
Drawings
FIG. 1 is a general schematic view of an aft turbine casing heat shield according to an embodiment of the present application;
FIG. 2 is a cross-sectional view of an aft turbine case heat shield according to an embodiment of the present application;
FIG. 3 is a heat shield bucket back schematic view of a turbine aft case heat shield according to an embodiment of the present application;
FIG. 4 is a heat shield bucket schematic view of an aft turbine case heat shield of an embodiment of the present application;
FIG. 5 is a schematic illustration of a support frame for an aft turbine case heat shield in accordance with an embodiment of the present application;
FIG. 6 is a side view of FIG. 5;
FIG. 7 is a heat shield assembly schematic view of a turbine aft case heat shield according to an embodiment of the present application;
FIG. 8 is a heat shield assembly schematic view of an aft turbine casing heat shield in accordance with an embodiment of the present application.
Wherein:
1-a heat shield; 11-heat shield blade back; 12-thermally insulated leaf pots; 2-a force bearing frame; 21-bearing support plate; 3-supporting a framework; 4-locking plate; 5-a second nut; 6-riveting; 7-bolt; 8-a first nut; 9-countersunk head screw.
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. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are some, but not all embodiments of the disclosure. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientation or positional relationship shown in the drawings, and are used for convenience in describing the present application and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application will be described in further detail with reference to fig. 1 to 8.
The application provides a turbine rear case separates heat exchanger, includes: force bearing frame 2, supporting framework 3 and heat shield 1.
Specifically, the force-bearing frame 2 comprises an outer end frame, an inner end frame and a force-bearing support plate 21 arranged between the outer end frame and the inner end frame; the supporting framework 3 is positioned behind the bearing support plate 21, one end of the supporting framework 3 is connected with the outer end frame of the bearing frame 2, and the other end of the supporting framework 3 is connected with the inner end frame of the bearing frame 2; thermal shroud 1 is streamlined, thermal shroud 1 cover is established in the outside of load support board 21, thermal shroud 1 comprises two parts, including thermal shroud leaf back 11 and thermal shroud leaf basin 12, the first end of thermal shroud leaf back 11 is connected with the first end of thermal shroud leaf basin 12, the second end of thermal shroud leaf back 11 and the second end of thermal shroud leaf basin 12 all are connected with supporting framework 3, thermal shroud leaf back 11, thermal shroud leaf basin 12 and supporting framework 3 enclose into a week, enclose around the outer periphery of load support board 21 of load support frame 2, can keep apart load support board 21 and gas, in order to play the effect that reduces load support board 21 surface temperature.
In one embodiment of the present application, the outrigger 21 has a parallelogram shape in cross-section, as shown in fig. 2.
In one embodiment of the application, the supporting framework 3 is fixedly connected with the outer end frame and the inner end frame of the force bearing frame 2 by adopting bolts 7 matched with first nuts 8.
As shown in fig. 3 to 4, the thermal shroud blade back 11 and the thermal shroud blade basin 12 of the thermal shroud rear casing thermal shroud of the present application are both a streamlined thin plate structure, and the wall thickness is generally set to 1mm to 2.5mm.
In an embodiment of the present application, by opening the countersunk bolt hole at the first end of the heat shield blade back 11, the first end of the heat shield blade basin 12 is provided with the nut component of looks adaptation, wherein, the nut component includes second nut 5, locking plate 4 and rivet 6, and second nut 5 is fixed at the first end of the heat shield blade basin 12 through locking plate 4 cooperation rivet 6, is connected the first end of the heat shield blade back 11 with the nut component of the heat shield blade basin 12 through countersunk bolt 9. In this embodiment, the first end of the heat shield blade back 11 is uniformly provided with 5 countersunk bolt holes along the radial direction, and the first end of the heat shield blade basin 12 is uniformly provided with 5 sets of nut assemblies along the radial direction, so that the connection reliability is improved.
Further, in an embodiment of the present application, countersunk bolt holes are respectively formed at the second end of the heat shield blade back 11 and the second end of the heat shield blade basin 12, a nut component is arranged on the support framework 3, and the second end of the heat shield blade back 11 and the second end of the heat shield blade basin 12 are connected with the nut component of the support framework 3 through countersunk screws 9. Advantageously, in this embodiment, as shown in fig. 5 to 6, the supporting framework 3 is a cuboid structure, two opposite sides of the supporting framework are respectively provided with grooves spaced from each other, the nut component is installed in the groove, the second end of the heat shield blade back 11 is connected with the nut component in the groove on one side of the supporting framework 3 through a countersunk screw 9, and the second end of the heat shield blade basin 12 is connected with the nut component in the groove on the other side of the supporting framework 3 through the countersunk screw 9.
The utility model provides a turbine rear casing separates heat exchanger, when the assembly, earlier fixes the supporting framework 3 on outer end frame, the interior end frame of load frame 2 through the bolt 7 and the first nut 8 of supporting framework 3 upper and lower two places, just is located the rear of load extension board 21. And then the second end of the heat shield blade back 11 and the second end of the heat shield blade basin 12 are assembled on the support framework 3 from two sides of the support framework 3, and are screwed and fixed with the second nut 5 on the support framework 3 through the countersunk head screw 9. Finally, as shown in fig. 8, after aligning the first end of the heat shield blade back 11 and the first end of the heat shield blade basin 12, the countersunk screws 9 are screwed and fixed to the second nuts 5 on the heat shield blade basin 12.
The rear turbine casing heat shield can finally realize the assembly and fixation among the heat shield blade back 11, the heat shield blade basin 12, the bearing frame 2 and the support framework 3 through the assembly process. Meanwhile, the thermal shield blade back 11 and the thermal shield blade basin 12 form a complete streamline thermal shield 1 which surrounds the outer periphery of the bearing support plate 21 of the bearing frame 2, and the bearing support plate 21 can be isolated from gas so as to play a role in reducing the surface temperature of the bearing support plate 21. The streamline heat shield 1 can be changed in appearance according to pneumatic design, and is not limited to the appearance shown in the figure.
The utility model provides a turbine rear casing separates heat exchanger can reduce bearing extension board 21 surface temperature, and then improves life, can effectively reduce the aerodynamic loss between 1.5% to 3% of gas runner to can reduce the engine oil consumption rate, make the engine use economic nature better.
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 (3)
1. A turbine aft case heat shield, comprising:
the bearing frame (2) comprises an outer end frame, an inner end frame and a bearing support plate (21) arranged between the outer end frame and the inner end frame;
the supporting framework (3) is positioned behind the bearing support plate (21), one end of the supporting framework (3) is connected with the outer end frame of the bearing frame (2), and the other end of the supporting framework is connected with the inner end frame of the bearing frame (2);
the heat shield (1) is streamline, the heat shield (1) is sleeved on the outer side of the bearing support plate (21), the heat shield (1) comprises a heat shield blade back (11) and a heat shield blade basin (12), the first end of the heat shield blade back (11) is connected with the first end of the heat shield blade basin (12), and the second end of the heat shield blade back (11) and the second end of the heat shield blade basin (12) are both connected with the support framework (3);
the supporting framework (3) is connected with the outer end frame and the inner end frame of the bearing frame (2) through bolts (7) matched with first nuts (8);
a countersunk bolt hole is formed in the first end of the heat insulation cover leaf back (11), a nut component is arranged at the first end of the heat insulation cover leaf basin (12), the nut component comprises a second nut (5), a locking plate (4) and a rivet (6), the second nut (5) is matched with the rivet (6) through the locking plate (4) and is fixed at the first end of the heat insulation cover leaf basin (12), and the first end of the heat insulation cover leaf back (11) is connected with the nut component of the heat insulation cover leaf basin (12) through a countersunk screw (9);
the first end of the heat shield blade back (11) is uniformly provided with 5 countersunk bolt holes along the radial direction, and the first end of the heat shield blade basin (12) is uniformly provided with 5 groups of nut assemblies along the radial direction;
countersunk bolt holes are formed in the second end of the heat shield blade back (11) and the second end of the heat shield blade basin (12), a nut component is arranged on the supporting framework (3), and the second end of the heat shield blade back (11) and the second end of the heat shield blade basin (12) are connected with the nut component of the supporting framework (3) through countersunk screws (9);
mutual spaced recess has been seted up respectively to the both sides of support chassis (3), nut unit installs in the recess, will through countersunk screw (9) the second end of heat shield leaf back of the body (11) with in the recess of support chassis (3) one side nut unit connects, will through countersunk screw (9) the second end of heat shield leaf basin (12) with in the recess of support chassis (3) opposite side nut unit connects.
2. The aft turbine case heat shield of claim 1, wherein the brace (21) is parallelogram-shaped in cross-section.
3. The aft turbine casing heat shield according to claim 1, wherein the wall thickness of the heat shield bucket back (11) and the heat shield bucket (12) are each 1mm to 2.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011133235.XA CN112211683B (en) | 2020-10-21 | 2020-10-21 | Thermal shield for turbine rear casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011133235.XA CN112211683B (en) | 2020-10-21 | 2020-10-21 | Thermal shield for turbine rear casing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112211683A CN112211683A (en) | 2021-01-12 |
| CN112211683B true CN112211683B (en) | 2022-11-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011133235.XA Active CN112211683B (en) | 2020-10-21 | 2020-10-21 | Thermal shield for turbine rear casing |
Country Status (1)
| Country | Link |
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| CN (1) | CN112211683B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103109045A (en) * | 2011-09-09 | 2013-05-15 | 三菱重工业株式会社 | Gas turbine |
| CN204610038U (en) * | 2015-05-18 | 2015-09-02 | 中国航空工业集团公司沈阳发动机设计研究所 | The heat insulation drag reducting cowling structure of a kind of support case support plate |
| CN106437884A (en) * | 2016-12-24 | 2017-02-22 | 贵州黎阳航空动力有限公司 | Long-service-life turbine bearing structure for gas turbine |
| CN106812626A (en) * | 2017-01-19 | 2017-06-09 | 中国航发沈阳发动机研究所 | Contain casing outside a kind of engine |
| CN207554126U (en) * | 2017-12-14 | 2018-06-29 | 中国航发沈阳发动机研究所 | A kind of combined type rear housing support plate dome structure and rear housing |
| CN110196167A (en) * | 2019-06-14 | 2019-09-03 | 中国航发沈阳发动机研究所 | Rear housing is used in a kind of test of core engine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9316108B2 (en) * | 2012-03-05 | 2016-04-19 | General Electric Company | Gas turbine frame stiffening rails |
| US20170067365A1 (en) * | 2015-09-09 | 2017-03-09 | General Electric Company | Exhaust frame strut with cooling fins |
| FR3093128B1 (en) * | 2019-02-25 | 2021-05-14 | Safran Aircraft Engines | Turbomachine housing |
-
2020
- 2020-10-21 CN CN202011133235.XA patent/CN112211683B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103109045A (en) * | 2011-09-09 | 2013-05-15 | 三菱重工业株式会社 | Gas turbine |
| CN204610038U (en) * | 2015-05-18 | 2015-09-02 | 中国航空工业集团公司沈阳发动机设计研究所 | The heat insulation drag reducting cowling structure of a kind of support case support plate |
| CN106437884A (en) * | 2016-12-24 | 2017-02-22 | 贵州黎阳航空动力有限公司 | Long-service-life turbine bearing structure for gas turbine |
| CN106812626A (en) * | 2017-01-19 | 2017-06-09 | 中国航发沈阳发动机研究所 | Contain casing outside a kind of engine |
| CN207554126U (en) * | 2017-12-14 | 2018-06-29 | 中国航发沈阳发动机研究所 | A kind of combined type rear housing support plate dome structure and rear housing |
| CN110196167A (en) * | 2019-06-14 | 2019-09-03 | 中国航发沈阳发动机研究所 | Rear housing is used in a kind of test of core engine |
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| Publication number | Publication date |
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| CN112211683A (en) | 2021-01-12 |
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Inventor after: Wang Tianyi Inventor after: Niu Juntao Inventor after: Zhang Qian Inventor after: Tang Xu Inventor after: Zhu Jian Inventor before: Wang Tianyi Inventor before: Niu Juntao Inventor before: Zhang Qian Inventor before: Tang Xu |
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