CN112179668A - Thermal state performance test protection device for gas turbine engine component - Google Patents
Thermal state performance test protection device for gas turbine engine component Download PDFInfo
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- CN112179668A CN112179668A CN202010990127.8A CN202010990127A CN112179668A CN 112179668 A CN112179668 A CN 112179668A CN 202010990127 A CN202010990127 A CN 202010990127A CN 112179668 A CN112179668 A CN 112179668A
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- 238000011056 performance test Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 66
- 238000009434 installation Methods 0.000 claims description 17
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 4
- 238000012545 processing Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 13
- 238000002485 combustion reaction Methods 0.000 description 12
- 230000008569 process Effects 0.000 description 11
- 230000000694 effects Effects 0.000 description 5
- 230000035882 stress Effects 0.000 description 4
- 230000008646 thermal stress Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
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- Testing Of Engines (AREA)
Abstract
The invention belongs to the field of gas turbine engines such as aviation, ships and ground gas turbines, and particularly relates to a thermal state performance test protection device for a gas turbine engine component. Comprises a first mounting edge, a distance rod, an elastic channel and a second mounting edge. The invention adopts a fixed distance compensation mode to replace the existing thermal state performance test design structure of the gas turbine engine component, so as to ensure that the gas turbine engine component is not damaged and reduce the test cost. In addition, by adopting the technical scheme of the invention, the gas turbine engine test part directly uses the engine to mount parts, thereby reducing the processing quantity of test parts, reducing the test cost, simulating the real working state of the test part and improving the accuracy of test data.
Description
Technical Field
The invention belongs to the field of gas turbine engines such as aviation, ships and ground gas turbines, and particularly relates to a thermal state performance test protection device for a gas turbine engine component.
Background
The gas turbine engine mainly comprises parts such as a gas compressor, a combustion chamber, a turbine, a spray pipe and the like, the turbofan type gas turbine also comprises afterburning and the like, the gas turbine engine bears high-temperature, high-pressure and other pneumatic loads in the working process, the working condition change is complex, the working environment is very severe, the combustion outlet temperature of the new generation of gas turbine engine is generally not less than 2000K, the outlet pressure of the gas compressor is not less than 3.0MPa, the working state and performance of the gas turbine engine parts cannot be accurately predicted by the existing theory, experience and calculation method, and a large amount of experimental research and verification are still needed to obtain the real performance of the engine parts in the current and long-term future. The test equipment and the air source capability of the gas turbine engine components are greatly developed after decades of development in China, the gap between the test equipment and the air source capability is smaller and smaller compared with that between the parts and the assemblies, and the test verification of different purposes can be carried out on the gas turbine engine components with different structural forms. With the continuous improvement of the air source capacity, in order to truly simulate the working state of the gas turbine engine component so as to achieve the purpose of performance assessment, the heating and pressurizing of the performance test of the gas turbine engine component are as close to the real working state as possible, so that the equipment load born by the test component is larger and larger, and the requirements on the test safety and the structural reliability of the test component are higher.
Taking a combustion chamber as an example, at present, part of combustion chamber component performance tests at home and abroad adopt a special thickened combustion chamber casing to absorb and transfer equipment loads, the combustion chamber casing is different from a real combustion chamber casing for installation, which may bring adverse effects on the accuracy of test results, and the combustion chamber casing cannot be used for assembling an engine and can only be used for component tests, thereby increasing the test cost. The main combustion chamber component for the installation is adopted in part of tests, but the main combustion chamber component only depends on free sliding design of test equipment (a rack) to transmit and absorb equipment load, and under the influence of factors such as equipment aging, sliding friction and pneumatic closure, the main combustion chamber component can bear certain equipment load, the test risk is high, the service life of the main combustion chamber component can be influenced, the reliability check of the component is adversely affected, and the thermal state performance tests of other gas turbine engine components also have the same problems.
Disclosure of Invention
As the gas turbine engine components and the test equipment bear high-temperature and high-pressure loads in the thermal state performance test process, and uncertain loads and thermal deformation are brought by the equipment, the test safety is possibly influenced. The invention provides a thermal state performance test protection device for a gas turbine engine component, which adopts a fixed distance compensation mode to replace the existing thermal state performance test design structure of the gas turbine engine component so as to ensure that the gas turbine engine component is not damaged and reduce the test cost.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
a thermal state performance test protection device for a gas turbine engine component comprises a first mounting edge, a distance rod, an elastic channel and a second mounting edge;
the first mounting edge and the second mounting edge are both provided with airflow through holes;
the distance rod is arranged between the first mounting edge and the second mounting edge, and at least one end of the distance rod is detachably mounted; one end of the elastic channel is installed on the first installation edge, and the other end of the elastic channel is installed on the gas turbine engine component, so that a sealing gas flow channel between the gas flow through hole on the first installation edge and the gas turbine engine component is formed, and the elastic channel is used for absorbing the thermal expansion axial displacement of the gas turbine engine component.
Further, the elastic channel is a corrugated ring.
Furthermore, the wave number of the corrugated ring is 1-5, the wave height is 20-100 mm, the wave thickness is 20-50 mm, the wall thickness is 1.5-5.0 mm, and the wave distance is 20-50 mm.
Furthermore, the distance rods are three or more groups.
Further, distance rod mounting holes are formed in the first mounting edge and the second mounting edge; the distance rod comprises a large-diameter part and two small-diameter parts arranged at two ends of the large-diameter part, and the two small-diameter parts are respectively installed in the distance rod installation holes of the first installation edge and the second installation edge.
Furthermore, the radius difference between the large diameter part and the small diameter part is 2-10 mm.
Further, the diameter of the large-diameter part is 20-50 mm.
By adopting the technical scheme, the invention can bring the following beneficial effects:
in the process of testing the thermal state performance of the gas turbine engine component, the invention can provide guarantee for testing the safety of the component and the repeated use of the engine, and comprises the following steps:
1) a test component protection box is formed between the first mounting edge and the second mounting edge, and the middle of the test component protection box is limited and supported by a distance rod to transfer equipment load and protect the test component from being influenced by external load;
2) the corrugated ring absorbs axial thermal deformation generated by thermal expansion in the thermal state test process of the gas turbine engine component, so that the thermal stress of the test component is reduced;
3) the corrugated ring compensates structural deformation and machining size deviation of the assembly matching part of the gas turbine engine component and the adjacent part, and reduces assembly stress;
4) the corrugated ring plays a certain damping role on vibration caused by test airflow pulsation, and the influence of test vibration stress is reduced;
in addition, by adopting the technical scheme of the invention, the gas turbine engine test part directly uses the engine to mount parts, thereby reducing the processing quantity of test parts, reducing the test cost, simulating the real working state of the test part and improving the accuracy of test data.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a thermal state performance test protection device and assembly of gas turbine engine components;
FIG. 2 is a schematic view of a spacer rod configuration;
FIG. 3 is a schematic view of a corrugated ring structure;
FIG. 4 is a schematic view of a single-section corrugated ring structure and deformation under force;
wherein: 1. a first mounting edge; 2. a distance rod; 3. a corrugated ring; 4. and a second mounting edge.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present disclosure, and the drawings only show the components related to the present disclosure rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
In one embodiment of the invention, as shown in fig. 1, a thermal state performance test protection device for a gas turbine engine component is provided, which comprises a first mounting edge 1, a distance rod 2, an elastic channel and a second mounting edge 4;
the first mounting edge 1 and the second mounting edge 4 are both provided with airflow through holes;
the distance rod 2 is arranged between the first mounting edge 1 and the second mounting edge 4, and at least one end of the distance rod is detachably mounted; one end of the elastic channel is installed on the first installation edge 1, and the other end of the elastic channel is installed on the gas turbine engine component, so that a sealing gas flow channel between the gas flow through hole on the first installation edge 1 and the gas turbine engine component is formed, and the elastic channel is used for absorbing the thermal expansion axial displacement of the gas turbine engine component.
In this embodiment, the elastic channel is a corrugated ring 3. The distance rods 2 are three or more groups. The first mounting edge 1 and the second mounting edge 4 are both provided with mounting holes for distance rods 2; the distance rod 2 comprises a large-diameter part and two small-diameter parts arranged at two ends of the large-diameter part, and the two small-diameter parts are respectively installed in the distance rod 2 installation holes of the first installation edge 1 and the second installation edge 4.
The first mounting edge 1 and the second mounting edge 4 are used as test equipment and test part assembly fixing adapter parts, the design thickness and the diameter are influenced by the test part of the gas turbine engine, the size of the test equipment and test state parameters, and the first mounting edge and the second mounting edge need to have certain structural strength, bear high-temperature and high-pressure pneumatic load of the test and absorb the reaction force of the deformed corrugated ring 3; and secondly, the load of the test equipment is transferred.
The distance rod 2 is of a rigid straight rod structure, and the structure and the processing technology are simple; considering machining tolerance and positioning effect, the radius difference H of the large-diameter part and the small-diameter part is controlled to be 2-10 mm, in the hot-state performance test process of the gas turbine engine component, the distance rods 2 mainly transfer equipment load and bear pressure, aiming at the hot-state performance test of the same component, the diameter D of each distance rod 2 is in inverse proportion to the number N, the number N of the distance rods 2 is selected to be 3-20, and the diameter D is controlled to be 20-50 mm.
The corrugated ring 3 can be assembled at the front end or the rear end of the gas turbine engine component and is used for absorbing thermal deformation generated by thermal expansion in the thermal state test process of the gas turbine engine component, so that the thermal stress of the test component can be greatly reduced, certain damping effect is realized on vibration caused by test airflow pulsation, the influence of the test vibration stress is reduced, and the gas turbine engine component is protected from being damaged in the thermal state performance test process. According to the diameter size of the inlet and outlet of the gas turbine engine component, the test pressure and temperature, whether a standard corrugated ring 3 or a special corrugated ring 3 is selected or not is determined according to the situation, and the maximum allowable axial deformation delta L of the corrugated ring 31Should be larger than the axial displacement deformation delta L generated by the thermal expansion in the test process of the gas turbine engine component2Influencing the axial deformation DeltaL of the corrugated ring 31Comprises a nominal diameter D0(depending on the structural dimensions of the gas turbine engine components, allowing optional addition of adapter parts), 3 wave number n of corrugated rings, wave height h, wave thickness a, wall thickness and wave distance t. The test protection device selects 3 wave numbers n of the corrugated rings to be controlled to be 1-5, the wave height h is 20-100 mm, the wave thickness a is 20-50 mm, the wall thickness is 1.5-5.0 mm, and the wave distance t is 20-50 mm.
In the test process, axial thermal stress generated by thermal expansion of test equipment and pneumatic load generated by gas flow are transmitted through the first mounting edge 1, the distance rod 2 and the second mounting edge 4, so that the test parts and components of the gas turbine engine are crossed to protect the test parts and components from being influenced by external load; meanwhile, the corrugated ring 3 is assembled at the front end or the rear end of the gas turbine engine component and is used for absorbing axial thermal deformation generated by thermal expansion in the thermal state test process of the gas turbine engine component through compression deformation, so that the thermal stress of the test component can be greatly reduced, certain damping effect is realized on vibration caused by test airflow pulsation, the influence of the test vibration stress is reduced, and the gas turbine engine component is protected from being damaged in the thermal state performance test process.
As shown in fig. 2, the distance rod 2 supports the first mounting edge 1 through a limiting spigot formed by a large diameter part and a small diameter part, the distance H of the limiting spigot is (D-D)/2, D is a standard thread diameter, and is fixedly connected with a flange through a bolt, and the distance rod 2 at the second mounting edge 4 is similar in structure.
As shown in fig. 3, the maximum allowable deformation Δ L of the corrugated ring 3 is influenced1The composition requirements of (A) mainly include the nominal diameter D0(depending on the structural dimensions of the gas turbine engine components, allowing optional addition of adapter parts), 3 wave number n of corrugated rings, wave height h, wave thickness a, wall thickness and wave distance t.
As shown in FIG. 4, the gas turbine engine test parts expand due to heat, increasing their length by Δ L2mm, due to the limiting function of the distance rod 2, the total length of the corrugated ring 3 and the test part is not changed, so that the corrugated ring 3 is compressed and deformed to absorb the elongation delta L of the test part2＝L1-L2＜ΔL1。
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure 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 disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides a gas turbine engine spare part hot state performance test protection device which characterized in that: the elastic fixing device comprises a first mounting edge, a distance rod, an elastic channel and a second mounting edge;
the first mounting edge and the second mounting edge are both provided with airflow through holes;
the distance rod is arranged between the first mounting edge and the second mounting edge, and at least one end of the distance rod is detachably mounted; one end of the elastic channel is installed on the first installation edge, and the other end of the elastic channel is installed on the gas turbine engine component, so that a sealing gas flow channel between the gas flow through hole on the first installation edge and the gas turbine engine component is formed, and the elastic channel is used for absorbing the thermal expansion axial displacement of the gas turbine engine component.
2. The test protection device of claim 1, wherein: the elastic channel is a corrugated ring.
3. The test protection device of claim 2, wherein: the wave number of the corrugated ring is 1-5, the wave height is 20-100 mm, the wave thickness is 20-50 mm, the wall thickness is 1.5-5.0 mm, and the wave distance is 20-50 mm.
4. The test protection device of claim 1, wherein: the distance rods are three groups or more than three groups.
5. The test protection device of claim 4, wherein: distance rod mounting holes are formed in the first mounting edge and the second mounting edge; the distance rod comprises a large-diameter part and two small-diameter parts arranged at two ends of the large-diameter part, and the two small-diameter parts are respectively installed in the distance rod installation holes of the first installation edge and the second installation edge.
6. The test protection device of claim 5, wherein: the radius difference between the large diameter part and the small diameter part is 2-10 mm.
7. The test protection device of claim 6, wherein: the diameter of the large-diameter part is 20-50 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010990127.8A CN112179668A (en) | 2020-09-18 | 2020-09-18 | Thermal state performance test protection device for gas turbine engine component |
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| CN202010990127.8A CN112179668A (en) | 2020-09-18 | 2020-09-18 | Thermal state performance test protection device for gas turbine engine component |
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| CN202010990127.8A Pending CN112179668A (en) | 2020-09-18 | 2020-09-18 | Thermal state performance test protection device for gas turbine engine component |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136649A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Flow distribution structure and method in simulation test of turbine engine combustor part |
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Application publication date: 20210105 |