CN114483312B - Turbine test air inlet section structure - Google Patents
Turbine test air inlet section structure Download PDFInfo
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- CN114483312B CN114483312B CN202210102909.2A CN202210102909A CN114483312B CN 114483312 B CN114483312 B CN 114483312B CN 202210102909 A CN202210102909 A CN 202210102909A CN 114483312 B CN114483312 B CN 114483312B
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- Prior art keywords
- inner ring
- cold air
- outer ring
- ring
- support plate
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Classifications
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of design of turbine test air inlet sections, and particularly relates to a turbine test air inlet section structure. Comprising the following steps: an outer ring, an inner ring, a support plate and a cold air pipe. An outer ring annular cavity is formed in the outer ring outer wall surface, an outer ring jet hole is formed in the outer ring outer wall surface opposite to the outer ring annular cavity, and an outer ring cold air tap is arranged in the outer ring annular cavity; the inner ring is nested in the outer ring, an air inlet channel is formed between the inner ring and the outer ring, an inner ring annular cavity is formed on the inner wall surface of the inner ring, an inner ring jet hole is formed on the outer wall surface of the inner ring opposite to the inner ring annular cavity, and an inner ring cold air nozzle is arranged on the inner ring annular cavity; the support plate is arranged in the air inlet channel between the inner ring and the outer ring, and through holes penetrating the outer ring, the air inlet channel and the inner ring are formed in the support plate; the cold air pipe is circulated with cold air, and comprises an outer ring cold air pipe and an inner ring cold air pipe, wherein the outer ring cold air pipe is connected with an outer ring cold air nozzle, and the inner ring cold air pipe passes through a through hole on the support plate and is connected with the inner ring cold air nozzle.
Description
Technical Field
The application belongs to the field of design of turbine test air inlet sections, and particularly relates to a turbine test air inlet section structure.
Background
The turbine inlet temperature in the aero-engine and the gas turbine presents obvious non-uniformity along the radial direction, and the temperature difference between the main flow and the end region can reach 100K-200K. In the existing turbine test without a combustion chamber, the outlet temperature of an air inlet section is uniformly distributed in the radial direction, the radial non-uniform distribution of the inlet temperature of a turbine in the whole machine environment is not considered, the influence of the radial non-uniform distribution of the temperature in a turbine flow field on the airflow angle of a blade is ignored, and then the matching relation with the flow of a downstream component cannot be accurately obtained, so that the turbine performance evaluated in the test is different from the turbine performance in the whole machine environment to some extent.
The test air inlet section is used as a part of the turbine tester and is connected with the air supply pipeline to the turbine inlet, so that the effect of transferring air flow is realized. The disadvantages of the current test air inlet section are represented by the following aspects:
(1) The air inlet section has single action and can only realize the action of transferring air flow;
(2) The radial distribution of the temperature transmitted to the turbine inlet is uniform, the radial uneven distribution trend of the temperature of the turbine inlet in the whole machine environment cannot be realized, and further the influence of the radial uneven temperature of the turbine inlet in the whole machine environment on the turbine performance cannot be considered.
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
The application aims to provide a turbine test air inlet section structure which solves at least one problem in the prior art.
The technical scheme of the application is as follows:
a turbine test inlet section structure comprising:
an outer ring, wherein an outer ring annular cavity is arranged on the outer wall surface of the outer ring, an outer ring jet hole is arranged on the outer wall surface of the outer ring opposite to the outer ring annular cavity, and an outer ring cold air tap is arranged on the outer ring annular cavity;
the inner ring is nested in the outer ring, an air inlet flow channel is formed between the inner ring and the outer ring, an inner ring annular cavity is formed in the inner wall surface of the inner ring, an inner ring jet hole is formed in the outer wall surface of the inner ring opposite to the inner ring annular cavity, and an inner ring cold air tap is arranged in the inner ring annular cavity;
the support plate is arranged in an air inlet flow passage between the inner ring and the outer ring, and is provided with a through hole penetrating through the outer ring, the air inlet flow passage and the inner ring;
the cold air pipe is provided with cold air in a circulating way, the cold air pipe comprises an outer ring cold air pipe and an inner ring cold air pipe, the outer ring cold air pipe is connected with the outer ring cold air nozzle, and the inner ring cold air pipe penetrates through the through hole on the support plate and is connected with the inner ring cold air nozzle.
In at least one embodiment of the present application, the centerlines of the outer ring jet hole, the outer ring cold air tap, the inner ring jet hole, and the inner ring cold air tap are all located at the same axial position.
In at least one embodiment of the application, the outer ring jet hole and the outer ring cold air tap are positioned at the outer ring straight section which is at least twice the chord length of the support plate behind the tail edge of the support plate;
the inner ring jet hole and the inner ring cold air tap are positioned at the inner ring straight section which is at least twice the chord length of the support plate behind the tail edge of the support plate.
In at least one embodiment of the application, the outer ring jet hole and the outer ring cold air tap are located at least 2.5 times the chordal length of the turbine vane upstream of the outer ring outlet location;
the inner ring jet aperture and the inner ring cold air tap are located at least 2.5 times the chord length of the turbine vane upstream of the inner ring outlet position.
In at least one embodiment of the present application, the support plate is a straight blade, and the support plate, the outer ring and the inner ring adopt a rounded corner design.
In at least one embodiment of the application, the support plates are uniformly arranged in the circumferential direction by 4 to 16.
In at least one embodiment of the application, the outer ring cold air nozzles and the outer ring cold air pipes are uniformly arranged along the circumferential direction, and the number of the outer ring cold air nozzles is consistent with that of the support plates;
the inner ring cold air nozzles and the inner ring cold air pipes are uniformly arranged along the circumferential direction, and the number of the inner ring cold air nozzles is consistent with that of the support plates.
In at least one embodiment of the present application, the outer ring cold air tap, the outer ring cold air pipe, the inner ring cold air tap, and the inner ring cold air pipe have diameters of 10mm to 40mm.
In at least one embodiment of the application, the length of the outer annular cavity and the inner annular cavity along the axial direction is 20 mm-80 mm, and the height is 10-40 mm.
In at least one embodiment of the present application, the outer ring of jet holes and the inner ring of jet holes are uniformly arranged in the circumferential direction by 20 to 40 and have a diameter of 2mm to 10mm.
The application has at least the following beneficial technical effects:
the turbine test air inlet section structure has the basic function of transferring air flow and the function of adjusting the radial distribution of the inlet temperature of the turbine, so that the radial distribution of the inlet temperature of the turbine is closer to the environment of the whole machine, and the turbine test performance is closer to the turbine performance in the environment of the whole machine.
Drawings
FIG. 1 is a schematic view of a turbine test inlet section according to one embodiment of the present application;
FIG. 2 is a cross-sectional view of a turbine test inlet section of one embodiment of the application;
FIG. 3 is a partial cross-sectional view of the turbine test inlet section structure of one embodiment of the application;
FIG. 4 is a schematic illustration of the relative positions of a cold air nozzle and a jet hole of a turbine test air intake section structure according to one embodiment of the present application;
FIG. 5 is a schematic cross-sectional view of a structural support plate for an inlet section of a turbine test according to one embodiment of the present application;
FIG. 6 is a schematic view of the relative positions of each unit in the circumferential direction of an inlet section structure for a turbine test according to one embodiment of the present application.
Wherein:
1-an outer ring; 11-an outer annular cavity; 12-an outer ring jet hole; 13-an outer ring cold air tap; 2-an inner ring; 21-an inner annular ring cavity; 22-inner ring jet holes; 23-an inner ring cold air tap; 3-supporting plates; 4-an outer ring cold air pipe; 5-inner ring cold air pipe.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying 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 described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the 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 should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 6.
The application provides a turbine test air inlet section structure, which comprises: an outer ring 1, an inner ring 2, a support plate 3 and a cold air pipe.
Specifically, the outer ring 1 and the inner ring 2 are respectively provided with an annular cavity, a jet hole and a cold air nozzle structure. The outer wall surface of the outer ring 1 is provided with an outer ring cavity 11, the outer wall surface of the outer ring 1 opposite to the outer ring cavity 11 is provided with an outer ring jet hole 12 communicated with the outer ring cavity 11, and the outer ring cavity 11 is provided with an outer ring cold air tap 13; the inner ring 2 is nested inside the outer ring 1, an air inlet channel is formed between the inner ring 2 and the outer ring 1, an inner ring annular cavity 21 is arranged on the inner wall surface of the inner ring 2, an inner ring jet hole 22 communicated with the inner ring annular cavity 21 is arranged on the outer wall surface of the inner ring 2 opposite to the inner ring annular cavity 21, and an inner ring cold air nozzle 23 is arranged on the inner ring annular cavity 21. The support plate 3 is arranged in an air inlet flow passage between the inner ring 2 and the outer ring 1, and through holes penetrating the outer ring 1, the air inlet flow passage and the inner ring 2 are formed in the support plate 3; the cold air pipe is circulated with cold air, and comprises an outer ring cold air pipe 4 and an inner ring cold air pipe 5, wherein the outer ring cold air pipe 4 is connected with an outer ring cold air nozzle 13, and the inner ring cold air pipe 5 passes through a through hole on the support plate 3 and is connected with an inner ring cold air nozzle 23.
According to the turbine test air inlet section structure, cold air is conveyed to the cold air nozzles of the outer ring 1 and the inner ring 2 through the cold air pipes, passes through the corresponding annular cavities, finally flows out of the jet holes to be mixed with the air inlet flow passage between the inner ring and the outer ring for main flow, and the purpose of adjusting the radial distribution of the inlet temperature of the turbine is achieved.
In the preferred embodiment of the present application, the cold air mixing effect can be improved by designing the jet holes and the positions of the cold air nozzles at the opposite distances from the support plate 3 and the outlet of the air inlet section. Referring to fig. 4, in this embodiment, the center lines of the outer ring jet hole 12, the outer ring cold air nozzle 13, the inner ring jet hole 22, and the inner ring cold air nozzle 23 are all located at the same axial position. The outer ring jet hole 12 and the outer ring cold air nozzle 13 are preferably positioned at the flat section of the outer ring 1, which is at least twice the chord length of the support plate 3, behind the tail edge of the support plate; the inner ring jet holes 22 and the inner ring cold air nozzles 23 are preferably located at the flat section of the inner ring 2 at least twice the chord length of the carrier 3 aft of the trailing edge thereof. The outer ring jet hole 12 and the outer ring cold air nozzle 13 are preferably positioned at least 2.5 times of the chord length of the turbine guide vane at the upstream of the outlet position of the outer ring 1; the inner ring jet hole 22 and the inner ring cold nozzle 23 are preferably located at least 2.5 times the chord length of the turbine vane upstream of the inner ring 2 outlet location.
In the preferred embodiment of the application, the support plate 3 is a straight blade, the support plate 3 is hollow so that the inner ring cold air pipe 5 passes through, the cross section of the support plate 3 is shown in fig. 5, and the support plate 3, the outer ring 1 and the inner ring 2 adopt a round-corner design. In this embodiment, the support plates 3 are preferably uniformly arranged in the circumferential direction, and the number is 4 to 16. Further, the outer ring cold air nozzles 13 and the outer ring cold air pipes 4 are uniformly arranged along the circumferential direction, and the number of the outer ring cold air nozzles is consistent with that of the support plates 3; the inner ring cold air nozzles 23 and the inner ring cold air pipes 5 are uniformly distributed along the circumferential direction, and the number of the inner ring cold air nozzles is consistent with that of the support plates 3.
In a preferred embodiment of the application, it is also necessary to rationally design the dimensions of the individual units. Specifically, in this embodiment, the diameters of the outer ring cold air nozzle 13, the outer ring cold air pipe 4, the inner ring cold air nozzle 23 and the inner ring cold air pipe 5 are preferably designed to be 10 mm-40 mm; the length of the outer ring cavity 11 and the inner ring cavity 21 along the axial direction is preferably designed to be 20 mm-80 mm, and the height is preferably designed to be 10-40 mm; the outer ring of jet holes 12 and the inner ring of jet holes 22 are evenly arranged in 20-40 in the circumferential direction, and the diameter of the jet holes is preferably designed to be 2-10 mm.
In one embodiment of the application, the specific number and circumferential relative positions of the individual units are seen in fig. 6.
According to the turbine test air inlet section structure, the radial distribution function of the inlet temperature of the turbine can be adjusted on the basis of ensuring the air flow transmission foundation of the air inlet section; by adjusting the temperature and the flow of the cold air, the radial uneven inflow of the inlet temperature is provided for the turbine test, the radial distribution trend of the inlet temperature of the turbine is consistent with the environment of the whole machine, and the performance of the turbine test is closer to the performance of the environment of the whole machine.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A turbine test inlet section structure comprising:
the outer ring (1), be provided with outer loop annular chamber (11) on outer wall of outer loop (1), offer outer loop jet aperture (12) on the outer wall of outer loop (1) opposite with outer loop annular chamber (11), be provided with outer loop cold air cock (13) on outer loop annular chamber (11);
the inner ring (2), the inner ring (2) is nested inside the outer ring (1), an air inlet channel is formed between the inner ring (2) and the outer ring (1), an inner ring annular cavity (21) is arranged on the inner wall surface of the inner ring (2), an inner ring jet hole (22) is formed on the outer wall surface of the inner ring (2) opposite to the inner ring annular cavity (21), and an inner ring cold air tap (23) is arranged on the inner ring annular cavity (21);
the support plate (3), the support plate (3) is arranged in an air inlet channel between the inner ring (2) and the outer ring (1), and through holes penetrating through the outer ring (1), the air inlet channel and the inner ring (2) are formed in the support plate (3);
the cold air pipe, it has the air conditioning to circulate in the cold air pipe, the cold air pipe includes outer loop cold air pipe (4) and inner ring cold air pipe (5), outer loop cold air pipe (4) with outer loop cold air cock (13) are connected, inner ring cold air pipe (5) pass through the last through-hole of extension board (3) with inner ring cold air cock (23) are connected.
2. The turbine test air intake section structure of claim 1, wherein the centerlines of the outer ring jet hole (12), the outer ring cold air nozzle (13), the inner ring jet hole (22) and the inner ring cold air nozzle (23) are all located at the same axial position.
3. Turbine test inlet section structure according to claim 2, characterized in that the outer ring jet holes (12) and the outer ring cold air nozzles (13) are located at the flat section of the outer ring (1) behind the trailing edge of the support plate (3) by at least twice the chord length of the support plate;
the inner ring jet hole (22) and the inner ring cold air nozzle (23) are positioned at the straight section of the inner ring (2) which is at least twice the chord length of the support plate (3) behind the tail edge of the support plate.
4. A turbine test inlet section structure according to claim 3, characterized in that the outer ring jet hole (12) and the outer ring cold air nozzle (13) are located at least 2.5 times the turbine vane chord length upstream of the outer ring (1) outlet position;
the inner ring jet hole (22) and the inner ring cold air nozzle (23) are positioned at least 2.5 times of the chord length of the turbine guide vane at the upstream of the outlet position of the inner ring (2).
5. The turbine test air inlet section structure according to claim 1, characterized in that the support plate (3) is a straight blade, and the support plate (3) and the outer ring (1) and the inner ring (2) adopt a rounded corner design.
6. The turbine test air inlet section structure according to claim 5, wherein the support plates (3) are uniformly arranged in the circumferential direction by 4 to 16.
7. The turbine test air inlet section structure according to claim 6, wherein the outer ring cold air nozzles (13) and the outer ring cold air pipes (4) are uniformly arranged along the circumferential direction, and the number of the outer ring cold air nozzles is consistent with that of the support plates (3);
the inner ring cold air nozzles (23) and the inner ring cold air pipes (5) are uniformly arranged along the circumferential direction, and the number of the inner ring cold air nozzles is consistent with that of the support plates (3).
8. Turbine test air inlet section structure according to claim 1, characterized in that the diameters of the outer ring cold air nozzle (13), the outer ring cold air pipe (4), the inner ring cold air nozzle (23) and the inner ring cold air pipe (5) are 10-40 mm.
9. Turbine test inlet section structure according to claim 1, characterized in that the length of the outer annular cavity (11) and the inner annular cavity (21) in the axial direction is 20-80 mm and the height is 10-40 mm.
10. The turbine test air inlet section structure according to claim 1, wherein the outer ring of jet holes (12) and the inner ring of jet holes (22) are uniformly arranged in the circumferential direction by 20-40 and have a diameter of 2-10 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210102909.2A CN114483312B (en) | 2022-01-27 | 2022-01-27 | Turbine test air inlet section structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210102909.2A CN114483312B (en) | 2022-01-27 | 2022-01-27 | Turbine test air inlet section structure |
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| Publication Number | Publication Date |
|---|---|
| CN114483312A CN114483312A (en) | 2022-05-13 |
| CN114483312B true CN114483312B (en) | 2023-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210102909.2A Active CN114483312B (en) | 2022-01-27 | 2022-01-27 | Turbine test air inlet section structure |
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Citations (5)
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| WO2004065763A2 (en) * | 2003-01-22 | 2004-08-05 | Vast Power Systems Inc. | Thermodynamic cycles using thermal diluent |
| EP2343443A2 (en) * | 2010-01-12 | 2011-07-13 | Kabushiki Kaisha Toshiba | Steam turbine |
| WO2013165281A1 (en) * | 2012-05-02 | 2013-11-07 | Gkn Aerospace Sweden Ab | Supporting structure for a gas turbine engine |
| CN109781421A (en) * | 2019-01-16 | 2019-05-21 | 中国航发沈阳发动机研究所 | A kind of rear measurement group section for loopful combustion chamber ignition performance test |
| CN214616798U (en) * | 2021-03-22 | 2021-11-05 | 中国航发商用航空发动机有限责任公司 | Core machine testing device |
-
2022
- 2022-01-27 CN CN202210102909.2A patent/CN114483312B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004065763A2 (en) * | 2003-01-22 | 2004-08-05 | Vast Power Systems Inc. | Thermodynamic cycles using thermal diluent |
| CN1764498A (en) * | 2003-01-22 | 2006-04-26 | 瓦斯特能量系统有限公司 | Reactor |
| EP2343443A2 (en) * | 2010-01-12 | 2011-07-13 | Kabushiki Kaisha Toshiba | Steam turbine |
| WO2013165281A1 (en) * | 2012-05-02 | 2013-11-07 | Gkn Aerospace Sweden Ab | Supporting structure for a gas turbine engine |
| CN109781421A (en) * | 2019-01-16 | 2019-05-21 | 中国航发沈阳发动机研究所 | A kind of rear measurement group section for loopful combustion chamber ignition performance test |
| CN214616798U (en) * | 2021-03-22 | 2021-11-05 | 中国航发商用航空发动机有限责任公司 | Core machine testing device |
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| 尾缘冷气喷射对超声涡轮叶栅性能的影响;王彬;黄康才;;燃气涡轮试验与研究(第04期);全文 * |
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| CN114483312A (en) | 2022-05-13 |
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