Adjustable stator blade sealing device of aero-engine

Abstract

The utility model provides an adjustable stator blade sealing device of an aero-engine, which is characterized in that an external shaft sleeve is arranged on a blade handle and rotates along with the blade handle; the internal shaft sleeve is mounted between the blade handle and the external shaft sleeve, the internal shaft sleeve is provided with a cavity, and a mounting shaft hole of the adjustable stator blade is matched with the cavity; a first sealing structure and a second sealing structure are arranged between the external shaft sleeve and the internal shaft sleeve, and the internal shaft sleeve and the external shaft sleeve are tightly sealed through cooperation of the first sealing structure and the second sealing structure. According to the utility model, a sealing mode of combining gas path sealing and labyrinth sealing is adopted, and the shaft sleeve at the blade handle and the bushing at the shaft hole of the casing are matched for sealing, so that the sealing performance of the gas compressor is improved, the water leakage problem at the VSV blade handle of the gas compressor is effectively reduced, the accuracy of T3 temperature change data is improved, and the reliability of a test result is enhanced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aero-engine, especially relates to an aero-engine adjustable stator vane sealing device. BACKGROUND

[0002] In the field of aero-engine, adjustable stator vane, abbreviated as VSV (Variable Stator Vane), is a stator vane that can change the installation angle according to the engine operating condition. The main purpose of applying VSV on the engine is to improve the stability of the engine and prevent surge. The VSV adjusting mechanism is used to drive the adjustable stator vane to rotate, change the installation angle of the adjustable stator vane, adjust the flow passage flow and the angle of attack of the rear grid airflow, so as to ensure the normal and stable work of the high-pressure compressor.

[0003] At present, the VSV adjusting mechanism is widely used in the high-pressure compressor of many types of aero-engines. In the actuation process of VSV, displacement in the rotation direction is generated with the compressor casing, so the design of gap cooperation is often used at the junction of the compressor casing and the VSV blade handle.

[0004] Figure 1 It is a sectional view of the structure at the VSV blade handle in the prior art. As shown in Figure 1 The shaft hole 10 is the VSV installation shaft hole on the compressor casing, the blade handle 11 is the adjustable stator vane blade handle part, the clamping device 12 is the clamping part of the VSV actuating mechanism for clamping the blade handle to rotate, the bushing 13 is the bushing between the VSV and the shaft hole, and the gap 14 is the gap cooperation between the bushing 13 and the blade handle 11.

[0005] In the rain absorption test of the aero-engine, the water intake of the core engine is often characterized by the temperature change of the total temperature (T3) at the inlet of the combustion chamber, and the relationship between the T3 temperature change and the water intake of the core engine is calibrated through the rain absorption test of the core engine. In the process of the core engine rain absorption test, the water injection amount of the core engine inlet is changed to obtain the temperature change of T3 under different water intake, so as to obtain the corresponding relationship between the water intake of the core engine and T3. It is found in the actual test process that water leakage occurs at the circumferential VSV blade handle gap, and after analysis, it is found that water leakage occurs at the gap cooperation of the VSV blade handle.

[0006] At the same time, it is found in the test that the adjustable stator vane of the compressor leaks a large amount of water due to the excessive gap design between the casing and the blade handle, and at the same time, gas also overflows.

[0007] As shown in Figure 1The water leakage at the intermediate gap 14 during the core engine rain ingestion test is shown by the arrow. The water leakage at the VSV blade stem during the test will result in the water amount reaching the combustion chamber inlet being less than the core engine inlet water amount, the actual T3 temperature change will not match the theoretical value, and the test data obtained is not accurate.

[0008] In addition, the water leakage at the blade stem gap also represents that a certain degree of air leakage will occur at this position, reducing the performance of the compressor.

[0009] Therefore, there is an urgent need in the art for a method to solve the VSV blade stem water leakage and air leakage problem, so as to obtain the accurate relationship between the core engine water intake and the T3 temperature change, and improve the performance of the compressor. Practical new type content

[0010] The technical problem to be solved by the present application is to overcome the defects of water leakage and air leakage at the VSV blade stem, and the inaccurate relationship between the core engine water intake and the T3 temperature change in the prior art, and to provide an aero-engine adjustable stator blade sealing device.

[0011] The technical problem is solved by the following technical scheme:

[0012] An aero-engine adjustable stator blade sealing device, characterized in that the aero-engine adjustable stator blade sealing device comprises:

[0013] An external shaft sleeve is mounted on the blade stem and rotates with the blade stem;

[0014] An internal shaft sleeve is mounted between the blade stem and the external shaft sleeve, and the internal shaft sleeve has a cavity, and the mounting shaft hole of the adjustable stator blade cooperates with the cavity;

[0015] A first sealing structure and a second sealing structure are arranged between the external shaft sleeve and the internal shaft sleeve, and the first sealing structure and the second sealing structure cooperate to seal between the internal shaft sleeve and the external shaft sleeve.

[0016] According to an embodiment of the present application, the external shaft sleeve and the blade stem are connected by threads.

[0017] According to an embodiment of the present application, the inner contact surface and the outer contact surface of the cavity of the internal shaft sleeve respectively cooperate with the shaft hole, so that the internal shaft sleeve is relatively stationary with the compressor casing.

[0018] According to an embodiment of the present application, the first sealing structure is arranged at the end of the external shaft sleeve, and the second sealing structure is arranged at the end of the internal shaft sleeve.

[0019] According to one embodiment of the utility model, the first sealing structure is set at the end of the inner shaft sleeve, and the second sealing structure is set at the end of the outer shaft sleeve.

[0020] According to one embodiment of the utility model, the first sealing structure is a sealing baffle, and the second sealing structure is a honeycomb sealing ring.

[0021] According to one embodiment of the utility model, a sealing cavity is formed between the upper part of the outer shaft sleeve and the upper part of the inner shaft sleeve.

[0022] According to one embodiment of the utility model, a sealing flow path is formed between the side part of the outer shaft sleeve and the side part of the inner shaft sleeve.

[0023] According to one embodiment of the utility model, the aero-engine adjustable stator blade sealing device further comprises a clamping device, which is installed on the blade handle and located above the outer shaft sleeve and used for clamping the blade handle to rotate.

[0024] The utility model has the positive progress effect that:

[0025] The utility model discloses an aero-engine adjustable stator blade sealing device, which adopts a sealing mode combining air path sealing and baffle sealing, and improves the sealing performance of the compressor by cooperating sealing of the shaft sleeve at the blade handle and the bushing at the shaft hole of the casing, effectively reduces the water leakage problem of the compressor VSV blade handle, improves the accuracy of T3 temperature change data, increases the effectiveness of core engine rain absorption test data, and enhances the reliability of test results. BRIEF DESCRIPTION OF DRAWINGS

[0026] The above and other features, properties and advantages of the utility model will become more apparent through the following description in combination with the drawings and embodiments, wherein the same reference signs always represent the same features, and the utility model discloses an aero-engine adjustable stator blade sealing device.

[0027] Figure 1 It is a sectional view of the structure of the VSV blade handle in the prior art.

[0028] Figure 2 It is a structural schematic view of the aero-engine adjustable stator blade sealing device.

[0029] Figure 3 It is a structural schematic view of the outer shaft sleeve in the aero-engine adjustable stator blade sealing device.

[0030] Figure 4 It is a structural schematic view of the inner bushing in the aero-engine adjustable stator blade sealing device. DETAILED DESCRIPTION

[0031] In order to make the above object, characteristics and advantages of the utility model more obvious and easy to understand, the specific implementation manners of the utility model will be described in detail below in combination with the drawings.

[0032] The embodiments of the utility model will be described in detail below with reference to the drawings. The preferred embodiments of the utility model will be described in detail below, and examples are shown in the drawings. In any possible case, the same signs will be used to represent the same or similar parts in all the drawings.

[0033] In addition, although the terms used in the utility model are selected from the commonly known and used terms, some terms mentioned in the utility model specification can be selected by the applicant according to his or her judgment, and the detailed meanings are described in the relevant part of the description herein.

[0034] In addition, the utility model should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0035] Figure 2 The structure schematic view of the adjustable stator blade sealing device of the aero-engine of the utility model. Figure 3 The structure schematic view of the outer shaft sleeve in the adjustable stator blade sealing device of the aero-engine of the utility model. Figure 4 The structure schematic view of the inner bushing in the adjustable stator blade sealing device of the aero-engine of the utility model.

[0036] As Figures 2 to 4 The utility model provides a kind of adjustable stator blade sealing device of aero-engine, it includes: outer shaft sleeve 20 and inner shaft sleeve 30.Outside sleeve 20 is installed on blade handle 40, rotates jointly with blade handle 40 actuation. Inner shaft sleeve 30 is installed between blade handle 40 and outer shaft sleeve 20, inner shaft sleeve 30 has cavity, and the mounting shaft hole 50 of adjustable stator blade cooperates with the cavity. First sealing structure 60 and second sealing structure 70 are arranged between outer shaft sleeve 20 and inner shaft sleeve 30, by first sealing structure 60 and second sealing structure 70 cooperation, so that inner shaft sleeve 30 and outer shaft sleeve 20 are sealed. Sealing refers to improving the sealing property of aero-engine by certain method and measure, to improve the performance of engine.

[0037] In addition, the adjustable stator blade sealing device of aero-engine further includes clamping device 80, clamping device 80 is installed on blade handle 40, located above outer shaft sleeve 20, for clamping blade handle 40 to rotate.

[0038] In this embodiment, the shaft hole 50 is a VSV installation shaft hole on the compressor casing, and the rest of the compressor casing has been omitted for ease of presentation. The blade stem 40 is the adjustable stator blade stem part, and the rest of the blade has been omitted for ease of presentation. The clamping device 80 is a VSV actuator mechanism for clamping the blade stem for rotation, and the rest of the actuator mechanism has been omitted for ease of presentation.

[0039] Preferably, the external shaft sleeve 20 and the blade stem 40 can be preferably connected by threads. The inner contact surface 31 and the outer contact surface 32 of the cavity of the internal shaft sleeve 30 are matched with the shaft hole 50, so that the internal shaft sleeve 30 is relatively stationary with the compressor casing.

[0040] The first sealing structure 60 can be preferably provided at the end of the external shaft sleeve 20, and the second sealing structure 70 is provided at the end of the internal shaft sleeve 30. Alternatively, the first sealing structure 60 is provided at the end of the internal shaft sleeve 30, and the second sealing structure 70 is provided at the end of the external shaft sleeve 20.

[0041] In this embodiment, the first sealing structure 60 can be preferably a sealing baffle, and the second sealing structure 70 can be preferably a honeycomb sealing ring. Of course, the first sealing structure 60 and the second sealing structure 70 can also use other sealing structures, and are not limited to sealing baffles and honeycomb sealing rings. Other sealing structures with sealing functions can also be used in combination, and are within the scope of the present application.

[0042] Through the cooperation between the first sealing structure 60 and the second sealing structure 70, a sealing cavity 100 is formed between the upper part of the external shaft sleeve 20 and the upper part of the internal shaft sleeve 30. A sealing flow path 200 is formed between the side of the external shaft sleeve 20 and the side of the internal shaft sleeve 30.

[0043] According to the above structure description, the adjustable stator blade sealing device of the aircraft engine of the present application, the external shaft sleeve 20 is the external shaft sleeve part of the adjustable stator blade sealing device, and is screwed with the blade stem 40 through the threads 21, and rotates together with the blade stem during the actuation process. The internal shaft sleeve 30 is the internal shaft sleeve part of the adjustable stator blade sealing device, and is matched with the shaft hole 50 through the outer contact surface 32 and the inner contact surface 31, and is relatively stationary with the compressor casing during the actuation process. The sealing baffle (i.e. the first sealing structure 60 or the second sealing structure 70) is located at the end of the external shaft sleeve 20, and the honeycomb sealing ring (i.e. the first sealing structure 60 or the second sealing structure 70) is located at the end of the internal shaft sleeve 30. The sealing cavity 100 is a sealing flow path formed between the external shaft sleeve 20 and the internal shaft sleeve 30.

[0044] The utility model discloses an aeroengine adjustable stator blade sealing device, and the air passage formed by the external shaft sleeve 20 and the internal bushing 30 forms the sealing flow path 200 and the sealing cavity 100, the air passage is formed by the sealing grate and the honeycomb sealing ring, and the adjustable stator blade sealing device is used for sealing the VSV blade stem gap.

[0045] During the core engine rain suction test, the aeroengine adjustable stator blade sealing device can effectively seal the compressor blade stem, reduce the compressor water leakage problem, improve the effectiveness of the test data, improve the compressor air tightness, and enhance the performance of the compressor.

[0046] In conclusion, the aeroengine adjustable stator blade sealing device adopts the sealing mode combining the air passage sealing and the grate sealing, the sealing performance of the compressor is improved through the cooperation of the shaft sleeve at the blade stem and the bushing at the casing shaft hole, the water leakage problem at the VSV blade stem of the compressor is effectively reduced, the accuracy of the T3 temperature change data is improved, the effectiveness of the core engine rain suction test data is increased, and the reliability of the test result is enhanced.

[0047] The aeroengine adjustable stator blade sealing device can also improve the VSV blade stem air leakage problem to a certain extent, reduce the compressor air leakage, and enhance the performance of the compressor. The aeroengine adjustable stator blade sealing device adopts the cooperation sealing mode, and the actuating space is reserved in the sealing device, so that the actuating process of the VSV is not affected, and the jamming condition is avoided.

[0048] The aeroengine adjustable stator blade sealing device is simple in part manufacturing, strong in universality, and can adopt the same bushing and shaft sleeve for the circumferential multiple shaft holes, thereby enhancing the universality. The adjustable stator blade sealing device is convenient to install and easy to disassemble and replace, and the cooperation mode adopted is simple, so that the disassembly and assembly can be easily carried out in the assembly process.

[0049] The aeroengine adjustable stator blade sealing device uses the bushing and the shaft sleeve in cooperation, adopts the sealing mode combining the air passage sealing and the grate sealing, can effectively improve the water leakage and air leakage problems of the VSV blade stem gap, and can not affect the normal actuation of the VSV through cooperation.

[0050] For those skilled in the art, the above invention is only an example and does not limit the application. Although it is not explicitly stated here, those skilled in the art can make various modifications, improvements and corrections to the application. Such modifications, improvements and corrections are suggested in the application, so such modifications, improvements and corrections still belong to the spirit and scope of the exemplary embodiments of the application.

[0051] Also, the use of "a" or "an" to describe an item or feature of the application should be understood to refer to one or more of the item or feature being described. As such, "a" or "an" should be understood to refer to at least one of the item or feature, and, similarly, "one or more" can be understood to refer to an implementation that includes one or more of the item or feature. The use of the term "or" in the context of "A or B" can be understood as a logical disjunction, such that "A or B" means any one of the items A or B, and if either or both of the items A and B are true (or exist), A or B is true (or exists). The term "and" in the context of "A and B" can be understood as a logical conjunction, such that "A and B" means both of the items A and B are true (or exist). The term "including" should be understood as meaning "including, but not limited to".

[0052] Similarly, it is to be noticed that the term "comprising", used in the context of describing the application, should not be interpreted as a limitation. To the contrary, the term "comprising" covers the presence of the item specified but also the possibility of additional items being present. The use of other terms such as "including", "consisting of", "consisting essentially of" and the like, should be understood as alternatives to "comprising" or "comprising", unless otherwise indicated.

[0053] Although the present application has been described with reference to specific implementations, it will be apparent to those skilled in the art that various modifications and changes can be made to these implementations without departing from the scope of the present application as set forth in the claims below. Accordingly, the disclosure of the present application is intended to be illustrative, but not limiting, of the scope of the application, which is set forth in the following claims.

Claims

1. An aircraft engine adjustable stator vane seal, comprising: The aero-engine variable stator blade sealing device comprises: an outer sleeve mounted on the blade stem and rotating with the blade stem; an inner sleeve mounted between the blade stem and the outer sleeve, the inner sleeve having a cavity, and the mounting shaft hole of the variable stator blade being matched with the cavity; first and second sealing structures are arranged between the outer sleeve and the inner sleeve, and the inner sleeve and the outer sleeve are sealed by the cooperation of the first and second sealing structures.

2. The aircraft engine adjustable stator vane seal of Claim 1, wherein, The outer sleeve and the blade stem are connected by threads.

3. The aircraft engine adjustable stator vane seal of claim 1, wherein, The inner contact surface and the outer contact surface of the cavity of the inner sleeve are matched with the shaft hole, so that the inner sleeve is relatively stationary with the compressor casing.

4. The aircraft engine adjustable stator vane seal of claim 1, wherein, The first sealing structure is arranged at the end of the outer sleeve, and the second sealing structure is arranged at the end of the inner sleeve.

5. The aircraft engine adjustable stator vane seal of claim 1, wherein, The first sealing structure is arranged at the end of the inner sleeve, and the second sealing structure is arranged at the end of the outer sleeve.

6. The aeroengine adjustable stator vane seal of claim 4 or 5, wherein, The first sealing structure is a sealing baffle, and the second sealing structure is a honeycomb sealing ring.

7. The aircraft engine adjustable stator vane seal of claim 4 or 5, wherein, The upper part of the outer sleeve and the upper part of the inner sleeve form a sealing cavity.

8. The aircraft engine adjustable stator vane seal of claim 4 or 5, wherein, The side of the outer sleeve and the side of the inner sleeve form a sealing flow path.

9. The aircraft engine adjustable stator vane seal of claim 1, wherein, The aero-engine variable stator blade sealing device further comprises a clamping device mounted on the blade stem above the outer sleeve for clamping the blade stem for rotation.

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