A test structure and method for the front and rear sealing structures of an aircraft engine high-pressure turbine

Abstract

The present application provides a test structure and method for the front and rear sealing structures of a high-pressure turbine of an aircraft engine. The structure is designed with a base, a supporting fan end, a high-pressure turbine simulation fan segment, and cooperates with a front sealing fan segment, a front locating pin, a front sealing spring, and a rear sealing fan segment. By adjusting the position, the structure can be in a main combustion chamber rear end sealing test state and a low-pressure turbine front end sealing test state, and can simulate the relative movement between the rear end of the main combustion chamber casing and the front end sealing fan segment, and between the front end of the low-pressure turbine casing and the rear end sealing fan segment along the axial and radial directions, as well as different matching states through an axial motion regulating screw and a radial motion regulating screw, so that the movement form, heat resistance, mechanical properties and sealing characteristics of the front end sealing fan segment and the rear end sealing fan segment can be conveniently observed and studied.

Description

Technical Field

[0001] The present application belongs to the technical field of testing the front and rear sealing structures of a high-pressure turbine of an aircraft engine, and specifically relates to a testing structure and method for the front and rear sealing structures of a high-pressure turbine of an aircraft engine. Background Art

[0002] The main combustion chamber 1, high-pressure turbine 2, and low-pressure turbine 3 in the aircraft engine are arranged in sequence. In order to ensure the sealing between the components, the front end outer wall of the high-pressure turbine 2 casing is designed to have a front end annular protrusion, and the outer edge of the front end annular protrusion is provided with a front end annular groove, the rear end outer wall is provided with a rear end annular protrusion, and the outer edge of the rear end annular protrusion is provided with a rear end annular groove, and a plurality of front end sealing sectors 4 are designed, front end sealing springs 5, front end locating pins 6, rear end sealing sectors 7, rear end sealing springs 8, and rear end locating pins 9. Among them, the inner edge of each front end sealing sector 4 extends into the front end annular groove and is spliced ​​with each other to form a front end sealing ring. The front end sealing ring and the front end annular groove are clearance-matched in the axial direction. The front end sealing sector 4 and the front end annular protrusion are circumferentially positioned by the front end locating pins 6, and the front end sealing spring 5 is sleeved on each front end locating pin 6. Each front end sealing spring 5 relies on elastic force to make each front end sealing sector 4 press against the rear end of the casing of the main combustion chamber 1 to form a floating seal, thereby realizing the sealing between the front end of the high-pressure turbine 2 and the rear end of the main combustion chamber 1; the inner edge of each rear end sealing sector 7 extends into the rear end annular groove and is spliced ​​together to form a rear end sealing ring, and the rear end sealing ring and the rear end annular groove are matched with each other in the axial direction. The rear end sealing sector 7 and the rear end annular protrusion are circumferentially positioned by the rear end positioning pin 9, and the rear end positioning pin 9 is sleeved with a rear end sealing spring 8. Each rear end sealing spring 8 relies on elastic force to make each rear end sealing sector 7 press against the front end of the casing of the low-pressure turbine 3 to form a floating seal, thereby realizing the sealing between the rear end of the high-pressure turbine 2 and the front end of the casing of the low-pressure turbine 3. There is a difference in radial height between the front and rear end sealing positions of the high-pressure turbine 2, such as Figure 1 shown.

[0003] When the aircraft engine is working, affected by changes in temperature and pressure, relative movement will occur in the axial and radial directions between each front sealing sector 4 and the rear end of the main combustion chamber 1 casing, and between each rear end sealing sector 7 and the front end of the low-pressure turbine 3 casing. In this process, the movement form of each front sealing sector 4 and the rear end sealing sector 7 may be axial translation or axial tilt. Different movement forms will directly affect the thrust, fuel consumption rate and other performance parameters of the aircraft engine. However, there is currently a lack of corresponding observation means to determine what kind of movement form it is, and there is a lack of effective means to study heat resistance, mechanical properties and sealing characteristics, making it difficult to provide support for the sealing design between the high-pressure turbine 2 and the main combustion chamber 1, and the low-pressure turbine 3.

[0004] This application is proposed in view of the current technical problems.

[0005] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0006] The purpose of this application is to provide a test structure and method for the front and rear sealing structures of an aircraft engine high-pressure turbine, so as to overcome or alleviate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] On the one hand, a test structure for the front and rear sealing structures of a high-pressure turbine of an aircraft engine is provided, comprising:

[0009] a base having a supporting protrusion thereon;

[0010] The fan end is supported, and the inner edge is connected to the base by a sliding rail. One side has a simulated fan section at the rear end of the main combustion chamber, and the other side has a simulated fan section at the front end of the low-pressure turbine.

[0011] The high-pressure turbine simulated sector has a sliding rail connection between the inner edge and the base, with a front end having a front sector-shaped protrusion and a rear end having a rear sector-shaped protrusion; the outer edge of the front sector-shaped protrusion has a front sector-shaped slot; the outer edge of the front sector-shaped protrusion has a rear sector-shaped slot;

[0012] The front sealing segment has an inner edge that extends into the front sector slot and is clearance-matched with the front sector slot in the axial direction;

[0013] Front end positioning pin, for circumferential positioning of the front end sector protrusion and the front end sealing sector;

[0014] The front sealing spring is sleeved on the front positioning pin;

[0015] The rear end sealing fan segment has an inner edge that extends into the rear end fan-shaped slot and is clearance-matched with the rear end fan-shaped slot in the axial direction;

[0016] The rear end positioning pin is used to circumferentially position the rear end fan-shaped protrusion and the rear end sealing sector;

[0017] The rear end sealing spring is sleeved on the rear end positioning pin;

[0018] An axial motion regulating screw is screwed onto the supporting protrusion;

[0019] The radial motion regulating screw is screwed between the base and the high-pressure turbine simulation sector;

[0020] The aero-engine high-pressure turbine front and rear sealing structure test structure has:

[0021] In the rear end sealing test state of the main combustion chamber, the rear end simulation sector of the main combustion chamber and the front end sealing sector are relatively arranged. The axial movement control screw is screwed against the support sector end, pushing the support sector end to slide, so that the rear end simulation sector of the main combustion chamber is close to the position of the front end sealing sector. The front end sealing spring relies on the elastic force to make the front end sealing sector press against the rear end simulation sector of the main combustion chamber to form a floating seal.

[0022] In the sealing test state of the front end of the low-pressure turbine, the front end simulation sector and the rear end sealing sector of the low-pressure turbine are relatively arranged, and the axial motion control screw is screwed against the supporting sector end, pushing the supporting sector end to slide, so that the front end simulation sector of the low-pressure turbine is close to the position of the rear end sealing sector, and the rear end sealing spring relies on elastic force to make the rear end sealing sector press against the front end simulation sector of the low-pressure turbine to form a floating seal.

[0023] According to at least one embodiment of the present application, in the aforementioned aircraft engine high-pressure turbine front and rear sealing structure test structure, positioning holes are provided on both sides of the support fan end;

[0024] The aero-engine high-pressure turbine front and rear sealing structure test structure is located at:

[0025] When the rear end of the main combustion chamber is in the sealing test state, the axial motion control screw extends into the positioning hole on the support fan end, which is located on the side of the simulated fan section at the front end of the low-pressure turbine;

[0026] When the front end of the low-pressure turbine is in the sealing test state, the axial motion control screw extends into the positioning hole on the supporting fan end located on the side of the simulated fan section at the rear end of the main combustion chamber.

[0027] On the other hand, a method for testing the front and rear seal structures of a high-pressure turbine of an aircraft engine is provided, comprising:

[0028] Main combustion chamber rear end sealing test steps:

[0029] The aircraft engine high-pressure turbine front and rear sealing structure test structure is set to the main combustion chamber rear end sealing test state;

[0030] Airflows of different temperatures, pressures and flow rates are introduced into the front sealing sector and the rear simulated sector of the main combustion chamber, and the supporting fan end is pushed to slide by turning the axial motion regulating screw, so that the rear simulated sector of the main combustion chamber and the front sealing sector undergo relative axial movement, so as to simulate the axial relative movement between the rear end of the main combustion chamber casing and the front sealing sector, and / or, by adjusting the radial motion regulating screw, the height of the high-pressure turbine simulated sector is changed, and then the height of the front sealing sector is changed, so that the rear simulated sector of the main combustion chamber and the front sealing sector undergo relative radial movement, so as to simulate the radial relative movement between the rear end of the main combustion chamber casing and the front sealing sector, and observe the movement form of the front sealing sector;

[0031] Airflows of different temperatures, pressures, and flows are introduced into the front sealing sector and the rear simulated sector of the main combustion chamber. The axial motion control screw is turned to push the support sector end to slide, thereby controlling the contact force between the rear simulated sector of the main combustion chamber and the front sealing sector. Furthermore, the radial motion control screw is adjusted to change the height of the high-pressure turbine simulated sector, thereby changing the height of the front sealing sector. This allows the rear simulated sector of the main combustion chamber and the front sealing sector to contact at different heights, thereby simulating different matching states between the rear end of the main combustion chamber casing and the front sealing sector, and studying the heat resistance and mechanical properties of the front sealing sector.

[0032] Airflows of varying temperatures, pressures, and flow rates were introduced into the front sealing sector and the simulated sector at the rear end of the main combustion chamber. The axial motion control screw was turned to push the support sector end to slide, and the radial motion control screw was adjusted to change the height of the simulated high-pressure turbine sector. This simulated the relative axial and radial motion between the rear end of the main combustion chamber casing and the front sealing sector, as well as different mating states, to study the sealing characteristics of the front sealing sector.

[0033] Low-pressure turbine front end sealing test steps:

[0034] Set the front and rear sealing structure test structure of the aircraft engine high-pressure turbine to the sealing test state of the front end of the low-pressure turbine;

[0035] Airflows of different temperatures, pressures, and flow rates are introduced into the rear end sealing sector and the front end simulation sector of the low-pressure turbine, and the supporting sector end is pushed to slide by turning the axial motion regulating screw, so that the front end simulation sector of the low-pressure turbine and the rear end sealing sector undergo relative axial motion, thereby simulating the axial relative motion between the front end and the rear end sealing sector of the low-pressure turbine casing, and / or, by adjusting the radial motion regulating screw, the height of the high-pressure turbine simulation sector is changed, thereby changing the height of the rear end sealing sector, thereby causing radial relative motion between the front end simulation sector of the low-pressure turbine and the rear end sealing sector, thereby simulating the radial relative motion between the front end and the rear end sealing sector of the low-pressure turbine casing, and observing the movement form of the rear end sealing sector;

[0036] Airflows of different temperatures, pressures, and flows are introduced into the rear end sealing sector and the front end simulated sector of the low-pressure turbine. The axial motion control screw is turned to push the support sector end to slide, thereby controlling the contact force between the front end simulated sector of the low-pressure turbine and the rear end sealing sector. Furthermore, the radial motion control screw is adjusted to change the height of the high-pressure turbine simulated sector, thereby changing the height of the rear end sealing sector. This allows the front end simulated sector of the low-pressure turbine and the rear end sealing sector to fit and contact at different heights, thereby simulating different fitting states between the front end and the rear end sealing sector of the low-pressure turbine casing, and studying the heat resistance and mechanical properties of the rear end sealing sector.

[0037] Airflows of different temperatures, pressures and flow rates are introduced into the rear end sealing sector and the front end simulated sector of the low-pressure turbine. The supporting fan end is pushed to slide by turning the axial motion control screw, and the height of the high-pressure turbine simulated sector is changed by adjusting the radial motion control screw to simulate the relative axial and radial movement between the front end of the low-pressure turbine casing and the rear end sealing sector, as well as different matching states, to study the sealing characteristics of the rear end sealing sector.

[0038] According to at least one embodiment of the present application, in the aforementioned method for testing the front and rear seal structures of a high-pressure turbine of an aircraft engine, during the main combustion chamber rear end seal test step, when airflows of different temperatures, pressures, and flow rates are introduced into the front seal sector and the main combustion chamber rear end simulated sector, a corresponding component is designed and bonded between the support sector end and the high-pressure turbine simulated sector to form a sealed cavity between the front seal sector and the main combustion chamber rear end simulated sector;

[0039] During the low-pressure turbine front end sealing test steps, when airflows of different temperatures, pressures, and flow rates are introduced into the rear end sealing sector and the low-pressure turbine front end simulation sector, corresponding components are designed and bonded between the supporting fan end and the high-pressure turbine simulation sector to form a closed cavity between the rear end sealing sector and the low-pressure turbine front end simulation sector. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 This is a schematic diagram of the front and rear sealing structures of the high-pressure turbine of an existing aircraft engine;

[0041] Figure 2 Schematic diagram of a test structure for the front and rear sealing structures of a high-pressure turbine of an aircraft engine provided by an embodiment of the present application in a state of sealing the rear end of a main combustion chamber;

[0042] Figure 3 Schematic diagram of a test structure for the front and rear sealing structures of a high-pressure turbine of an aircraft engine provided by an embodiment of the present application in a state of sealing the front end of a low-pressure turbine;

[0043] in:

[0044] 1-main combustion chamber; 2-high-pressure turbine; 3-low-pressure turbine; 4-front-end sealing sector; 5-front-end sealing spring; 6-front-end positioning pin; 7-rear-end sealing sector; 8-rear-end sealing spring; 9-rear-end positioning pin; 10-base; 11-support sector end; 12-high-pressure turbine simulation sector; 13-axial motion control screw; 14-radial motion control screw.

[0045] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0046] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0047] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0048] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0049] The following is combined with Figures 1 to 3 This application is described in further detail.

[0050] On the one hand, a test structure for the front and rear sealing structures of a high-pressure turbine of an aircraft engine is provided, comprising:

[0051] A base 10 having a supporting protrusion thereon;

[0052] The inner edge of the support fan end 11 is connected to the base 10 by a sliding rail, with one side having a simulated fan section at the rear end of the main combustion chamber and the other side having a simulated fan section at the front end of the low-pressure turbine;

[0053] The high-pressure turbine simulation sector 12 is connected to the base 10 by a slide rail between its inner edge, and has a front sector-shaped protrusion at the front end and a rear sector-shaped protrusion at the rear end; the outer edge of the front sector-shaped protrusion has a front sector-shaped slot; the outer edge of the front sector-shaped protrusion has a rear sector-shaped slot;

[0054] The front sealing sector 4 has an inner edge that extends into the front sector slot and is clearance-matched with the front sector slot in the axial direction;

[0055] The front end positioning pin 6 is used to circumferentially position the front end sector protrusion and the front end sealing sector 4;

[0056] The front sealing spring 5 is sleeved on the front positioning pin 6;

[0057] The inner edge of the rear end sealing segment 7 extends into the rear end fan-shaped slot and is in axial clearance fit with the rear end fan-shaped slot;

[0058] The rear end positioning pin 9 is used to circumferentially position the rear end sector protrusion and the rear end sealing sector 7;

[0059] The rear end sealing spring 8 is sleeved on the rear end positioning pin 9;

[0060] An axial motion regulating screw 13 is screwed onto the supporting protrusion;

[0061] The radial motion regulating screw 14 is screwed between the base 10 and the high-pressure turbine simulation sector 12;

[0062] The aero-engine high-pressure turbine front and rear sealing structure test structure has:

[0063] In the rear end sealing test state of the main combustion chamber, the rear end simulation sector of the main combustion chamber and the front end sealing sector 4 are arranged relative to each other. The axial movement control screw 13 is screwed against the support sector end 11, pushing the support sector end 11 to slide, so that the rear end simulation sector of the main combustion chamber approaches the position of the front end sealing sector 4. The front end sealing spring 5 relies on the elastic force to make the front end sealing sector 4 abut against the rear end simulation sector of the main combustion chamber to form a floating seal;

[0064] In the sealing test state of the front end of the low-pressure turbine, the front end simulation sector of the low-pressure turbine and the rear end sealing sector 7 are relatively arranged. The axial motion control screw 13 is screwed against the supporting sector end 11, pushing the supporting sector end 11 to slide, so that the front end simulation sector of the low-pressure turbine is close to the position of the rear end sealing sector 7. The rear end sealing spring 8 relies on elastic force to make the rear end sealing sector 7 rest on the front end simulation sector of the low-pressure turbine to form a floating seal.

[0065] As for the test structure of the front and rear sealing structures of the high-pressure turbine of the aircraft engine disclosed in the above-mentioned embodiment, technical personnel in the field can understand that it is designed with a base 10, a supporting fan end 11, and a high-pressure turbine simulation fan segment 12, which cooperates with the front end sealing fan segment 4, the front end positioning pin 6, the front end sealing spring 5, and the rear end sealing fan segment 7. By adjusting the position, it can be in the rear end sealing test state of the main combustion chamber and the front end sealing test state of the low-pressure turbine, and can simulate the relative movement between the rear end of the main combustion chamber 1 casing and the front end sealing fan segment 4, and between the front end of the low-pressure turbine 3 casing and the rear end sealing fan segment 7, along the axial and radial directions, as well as different matching states through the axial movement control screw 13 and the radial movement control screw 14, so that the movement form, heat resistance, mechanical properties and sealing characteristics of the front end sealing fan segment 4 and the rear end sealing fan segment 7 can be conveniently observed and studied. The specific process can refer to the test method of the front and rear sealing structures of the high-pressure turbine of the aircraft engine disclosed in the embodiment of the present application.

[0066] In some optional embodiments, in the above-mentioned aircraft engine high-pressure turbine front and rear sealing structure test structure, positioning holes are provided on both sides of the support fan end 11;

[0067] The aero-engine high-pressure turbine front and rear sealing structure test structure is located at:

[0068] When the rear end of the main combustion chamber is in the sealing test state, the axial movement control screw 13 extends into the positioning hole on the support fan end 11 located on the side of the simulated fan section at the front end of the low-pressure turbine;

[0069] When the front end of the low-pressure turbine is in a sealing test state, the axial motion regulating screw 13 extends into a positioning hole on the support fan end 11 located on one side of the simulated fan section at the rear end of the main combustion chamber.

[0070] On the other hand, a method for testing the front and rear seal structures of a high-pressure turbine of an aircraft engine is provided, comprising:

[0071] Main combustion chamber rear end sealing test steps:

[0072] The aircraft engine high-pressure turbine front and rear sealing structure test structure is set to the main combustion chamber rear end sealing test state;

[0073] Airflows of different temperatures, pressures and flows are introduced into the front sealing sector 4 and the rear end simulation sector of the main combustion chamber, and the supporting sector end 11 is pushed to slide by twisting the axial motion regulating screw 13, so that relative axial movement occurs between the rear end simulation sector of the main combustion chamber and the front end sealing sector 4, so as to simulate the axial relative movement between the rear end of the casing of the main combustion chamber 1 and the front end sealing sector 4, and / or, by adjusting the radial motion regulating screw 14, the height of the high-pressure turbine simulation sector 12 is changed, and then the height of the front end sealing sector 4 is changed, so that relative radial movement occurs between the rear end simulation sector of the main combustion chamber and the front end sealing sector 4, so as to simulate the radial relative movement between the rear end of the casing of the main combustion chamber 1 and the front end sealing sector 4, and observe the movement form of the front end sealing sector 4;

[0074] Airflows of different temperatures, pressures, and flows are introduced into the front sealing sector 4 and the rear simulated sector of the main combustion chamber. The support sector end 11 is pushed to slide by turning the axial motion control screw 13 to control the contact force between the rear simulated sector of the main combustion chamber and the front sealing sector 4. In addition, the height of the high-pressure turbine simulated sector 12 is changed by adjusting the radial motion control screw 14, thereby changing the height of the front sealing sector 4. This allows the rear simulated sector of the main combustion chamber and the front sealing sector 4 to fit in contact at different heights, thereby simulating different fitting states between the rear end of the casing of the main combustion chamber 1 and the front sealing sector 4, and studying the heat resistance and mechanical properties of the front sealing sector 4.

[0075] Airflows of varying temperatures, pressures, and flow rates were introduced into the front sealing sector 4 and the simulated sector at the rear end of the main combustion chamber. The support sector end 11 was pushed to slide by turning the axial motion control screw 13, and the height of the high-pressure turbine simulated sector 12 was changed by adjusting the radial motion control screw 14. This simulated the relative axial and radial motion between the rear end of the main combustion chamber 1 casing and the front sealing sector 4, as well as different mating states, to study the sealing characteristics of the front sealing sector 4.

[0076] Low-pressure turbine front end sealing test steps:

[0077] Set the front and rear sealing structure test structure of the aircraft engine high-pressure turbine to the sealing test state of the front end of the low-pressure turbine;

[0078] Airflows of different temperatures, pressures, and flows are introduced into the rear end sealing sector 7 and the front end simulation sector of the low-pressure turbine, and the supporting sector end 11 is pushed to slide by twisting the axial motion regulating screw 13, so that relative axial movement occurs between the front end simulation sector of the low-pressure turbine and the rear end sealing sector 7, so as to simulate the relative axial movement between the front end and the rear end sealing sector 7 of the low-pressure turbine 3 casing, and / or, by adjusting the radial motion regulating screw 14, the height of the high-pressure turbine simulation sector 12 is changed, and then the height of the rear end sealing sector 7 is changed, so that relative radial movement occurs between the front end simulation sector of the low-pressure turbine and the rear end sealing sector 7, so as to simulate the relative radial movement between the front end and the rear end sealing sector 7 of the low-pressure turbine 3 casing, and observe the movement form of the rear end sealing sector 7;

[0079] Airflows of different temperatures, pressures, and flows are introduced into the rear end sealing sector 7 and the front end simulation sector of the low-pressure turbine. The support sector end 11 is pushed to slide by turning the axial motion regulating screw 13 to control the contact force between the front end simulation sector of the low-pressure turbine and the rear end sealing sector 7. Furthermore, the height of the high-pressure turbine simulation sector 12 is changed by adjusting the radial motion regulating screw 14, thereby changing the height of the rear end sealing sector 7. This allows the front end simulation sector of the low-pressure turbine and the rear end sealing sector 7 to fit in contact at different heights, thereby simulating different fitting states between the front end of the low-pressure turbine 3 casing and the rear end sealing sector 7, and studying the heat resistance and mechanical properties of the rear end sealing sector 7.

[0080] Airflows of different temperatures, pressures and flows are introduced into the rear end sealing sector 7 and the front end simulation sector of the low-pressure turbine. The supporting fan end 11 is pushed to slide by turning the axial motion regulating screw 13, and the height of the high-pressure turbine simulation sector 12 is changed by adjusting the radial motion regulating screw 14 to simulate the axial and radial relative movement between the front end of the low-pressure turbine 3 casing and the rear end sealing sector 7, as well as different fitting states, to study the sealing characteristics of the rear end sealing sector 7.

[0081] In some optional embodiments, in the above-mentioned method for testing the front and rear sealing structures of the aircraft engine high-pressure turbine, during the main combustion chamber rear end sealing test step, when airflows of different temperatures, pressures, and flow rates are introduced into the front sealing sector 4 and the main combustion chamber rear end simulated sector, corresponding components are designed and bonded between the support sector end 11 and the high-pressure turbine simulated sector 12 to form a sealed cavity between the front sealing sector 4 and the main combustion chamber rear end simulated sector;

[0082] During the low-pressure turbine front end sealing test step, when airflows of different temperatures, pressures, and flow rates are introduced into the rear end sealing sector 7 and the low-pressure turbine front end simulation sector, corresponding components are designed and bonded between the supporting fan end 11 and the high-pressure turbine simulation sector 12 to form a closed cavity between the rear end sealing sector 7 and the low-pressure turbine front end simulation sector.

[0083] The test method for the front and rear sealing structures of the aircraft engine high-pressure turbine disclosed in the above embodiment is implemented based on the test structure for the front and rear sealing structures of the aircraft engine high-pressure turbine disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the test structure part of the front and rear sealing structures of the aircraft engine high-pressure turbine. Its technical effects can also refer to the technical effects of the relevant parts of the test structure of the front and rear sealing structures of the aircraft engine high-pressure turbine, which will not be repeated here.

[0084] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0085] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A test structure for the front and rear sealing structures of an aircraft engine high-pressure turbine, characterized in that: include: A base (10) having a supporting protrusion thereon; The support fan end (11) is connected to the base (10) by a slide rail, and one side has a main combustion chamber rear end simulation fan section, and the other side has a low-pressure turbine front end simulation fan section; The high-pressure turbine simulation sector (12) is connected to the base (10) by a slide rail between its inner edge and the front end thereof, and has a front end sector-shaped protrusion and a rear end sector-shaped protrusion; the outer edge of the front end sector-shaped protrusion has a front end sector-shaped slot; the outer edge of the front end sector-shaped protrusion has a rear end sector-shaped slot; The front sealing fan section (4) has an inner edge extending into the front fan-shaped slot and is clearance-matched with the front fan-shaped slot in the axial direction; A front end positioning pin (6) is used to circumferentially position the front end sector protrusion and the front end sealing sector (4); A front end sealing spring (5) is sleeved on the front end positioning pin (6); The rear end sealing fan section (7) has an inner edge extending into the rear end fan-shaped slot and is clearance-matched with the rear end fan-shaped slot in the axial direction; A rear end positioning pin (9) is used to circumferentially position the rear end sector protrusion and the rear end sealing sector (7); A rear end sealing spring (8) is sleeved on the rear end positioning pin (9); An axial motion regulating screw (13) is screwed onto the supporting protrusion; A radial motion regulating screw (14) is screwed between the base (10) and the high-pressure turbine simulation sector (12); The aero-engine high-pressure turbine front and rear sealing structure test structure has: In the main combustion chamber rear end sealing test state, the main combustion chamber rear end simulation sector and the front end sealing sector (4) are relatively arranged, the axial movement control screw (13) is screwed against the support sector end (11), and the support sector end (11) is pushed to slide, so that the main combustion chamber rear end simulation sector approaches the front end sealing sector (4), and the front end sealing spring (5) relies on the elastic force to make the front end sealing sector (4) abut against the main combustion chamber rear end simulation sector to form a floating seal; In the front end sealing test state of the low-pressure turbine, the front end simulation sector of the low-pressure turbine and the rear end sealing sector (7) are relatively arranged, and the axial motion control screw (13) is screwed against the support sector end (11), pushing the support sector end (11) to slide, so that the front end simulation sector of the low-pressure turbine approaches the position of the rear end sealing sector (7), and the rear end sealing spring (8) relies on the elastic force to make the rear end sealing sector (7) abut against the front end simulation sector of the low-pressure turbine to form a floating seal.

2. The aircraft engine high-pressure turbine front and rear sealing structure test structure according to claim 1, characterized in that: There are positioning holes on both sides of the supporting fan end (11); The aero-engine high-pressure turbine front and rear sealing structure test structure is located at: When the rear end of the main combustion chamber is in a sealing test state, the axial movement regulating screw (13) extends into a positioning hole on the support fan end (11) located on one side of the simulated fan section at the front end of the low-pressure turbine; When the front end of the low-pressure turbine is in a sealing test state, the axial motion regulating screw (13) extends into a positioning hole on the supporting fan end (11) located on one side of the simulated fan section at the rear end of the main combustion chamber.

3. A method for testing the front and rear sealing structures of a high-pressure turbine of an aircraft engine, based on the test structure for the front and rear sealing structures of a high-pressure turbine of an aircraft engine according to claim 2, characterized in that: include: Main combustion chamber rear end sealing test steps: The aircraft engine high-pressure turbine front and rear sealing structure test structure is set to the main combustion chamber rear end sealing test state; Airflows of different temperatures, pressures and flows are introduced into the front end sealing segment (4) and the rear end simulation segment of the main combustion chamber, and the supporting segment (11) is pushed to slide by turning the axial motion regulating screw (13), so that the rear end simulation segment of the main combustion chamber and the front end sealing segment (4) undergo relative axial motion, thereby simulating the axial relative motion between the rear end of the casing of the main combustion chamber (1) and the front end sealing segment (4), and / or, by adjusting the radial motion regulating screw (14), the height of the high pressure turbine simulation segment (12) is changed, thereby changing the height of the front end sealing segment (4), so that the rear end simulation segment of the main combustion chamber and the front end sealing segment (4) undergo relative radial motion, thereby simulating the radial relative motion between the rear end of the casing of the main combustion chamber (1) and the front end sealing segment (4), and observing the motion form of the front end sealing segment (4); Airflows of different temperatures, pressures, and flows are introduced into the front end sealing segment (4) and the rear end simulation segment of the main combustion chamber, and the supporting segment (11) is pushed to slide by turning the axial motion regulating screw (13) to control the contact force between the rear end simulation segment of the main combustion chamber and the front end sealing segment (4). Furthermore, the height of the high pressure turbine simulation segment (12) is changed by adjusting the radial motion regulating screw (14), thereby changing the height of the front end sealing segment (4), so that the rear end simulation segment of the main combustion chamber and the front end sealing segment (4) are in contact with each other at different heights, thereby simulating different matching states between the rear end of the casing of the main combustion chamber (1) and the front end sealing segment (4), and studying the heat resistance and mechanical properties of the front end sealing segment (4); Airflows of different temperatures, pressures, and flows are introduced into the front sealing segment (4) and the rear end simulation segment of the main combustion chamber. The support segment (11) is pushed to slide by turning the axial motion control screw (13). Furthermore, the height of the high-pressure turbine simulation segment (12) is changed by adjusting the radial motion control screw (14) to simulate the relative movement along the axial and radial directions between the rear end of the casing of the main combustion chamber (1) and the front sealing segment (4), as well as different matching states, to study the sealing characteristics of the front sealing segment (4). Low-pressure turbine front end sealing test steps: Set the front and rear sealing structure test structure of the aircraft engine high-pressure turbine to the sealing test state of the front end of the low-pressure turbine; Airflows of different temperatures, pressures, and flows are introduced into the rear end sealing section (7) and the front end simulation section of the low-pressure turbine, and the support section (11) is pushed to slide by turning the axial motion regulating screw (13), so that the front end simulation section of the low-pressure turbine and the rear end sealing section (7) undergo relative axial motion, thereby simulating the relative axial motion between the front end of the low-pressure turbine (3) casing and the rear end sealing section (7), and / or, by adjusting the radial motion regulating screw (14), the height of the high-pressure turbine simulation section (12) is changed, thereby changing the height of the rear end sealing section (7), so that the front end simulation section of the low-pressure turbine and the rear end sealing section (7) undergo relative radial motion, thereby simulating the relative radial motion between the front end of the low-pressure turbine (3) casing and the rear end sealing section (7), and observing the motion form of the rear end sealing section (7); Airflows of different temperatures, pressures, and flows are introduced into the rear end sealing segment (7) and the front end simulation segment of the low-pressure turbine. The support segment (11) is pushed to slide by turning the axial motion control screw (13) to control the contact force between the front end simulation segment of the low-pressure turbine and the rear end sealing segment (7). Furthermore, the height of the high-pressure turbine simulation segment (12) is changed by adjusting the radial motion control screw (14), thereby changing the height of the rear end sealing segment (7) so that the front end simulation segment of the low-pressure turbine and the rear end sealing segment (7) are in contact with each other at different heights, thereby simulating different matching states between the front end of the low-pressure turbine (3) casing and the rear end sealing segment (7), and studying the heat resistance and mechanical properties of the rear end sealing segment (7). Airflows of different temperatures, pressures and flows are introduced into the rear end sealing sector (7) and the front end simulation sector of the low-pressure turbine. The support sector (11) is pushed to slide by turning the axial motion regulating screw (13). In addition, the height of the high-pressure turbine simulation sector (12) is changed by adjusting the radial motion regulating screw (14) to simulate the relative movement between the front end of the low-pressure turbine (3) casing and the rear end sealing sector (7) in the axial and radial directions, as well as different matching states, to study the sealing characteristics of the rear end sealing sector (7).

4. The method for testing the front and rear seal structures of a high-pressure turbine of an aircraft engine according to claim 3, characterized in that: In the main combustion chamber rear end sealing test step, when airflows of different temperatures, pressures, and flows are introduced into the front end sealing sector (4) and the main combustion chamber rear end simulation sector, corresponding components are designed and bonded between the support sector (11) and the high-pressure turbine simulation sector (12), forming a sealed cavity between the front end sealing sector (4) and the main combustion chamber rear end simulation sector; In the low-pressure turbine front end sealing test step, when airflows of different temperatures, pressures, and flows are introduced into the rear end sealing sector (7) and the low-pressure turbine front end simulation sector, corresponding components are designed and bonded between the supporting sector (11) and the high-pressure turbine simulation sector (12), forming a closed cavity between the rear end sealing sector (7) and the low-pressure turbine front end simulation sector.

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