Inlet guide vane inner ring holding device, gas compressor and aero-engine

Abstract

The invention discloses an inlet guide vane inner ring holding device, a gas compressor and an aero-engine, and the inlet guide vane inner ring holding device comprises a casing and an inner ring; at least one part of one end, facing the casing, of the inner ring is mounted in the casing; the inlet guide vane is mounted on the inner ring; one of the casing and the inner ring is provided with a plurality of bosses arranged along the circumferential direction, and the other one is provided with a plurality of grooves arranged along the circumferential direction; a first working face and a second working face which are matched with each other are arranged on the two sides of the boss and the two sides of the groove respectively, and angles are formed between the two working faces and the tangent line in the circumferential direction. By means of the technical scheme, axial positioning of the casing and the inner ring can be achieved, resistance for resisting eccentricity can be generated between working faces, the adjusting precision of the inlet guide vane and the smoothness of a flow channel in the test process can be effectively improved, the consistency of the aerodynamic performance of the inlet guide vane is guaranteed, and the service life of the inlet guide vane is prolonged. And the aerodynamic performance of the high-pressure compressor is improved to a certain extent.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engine guide vane adjustment, and in particular relates to an inlet guide vane inner ring retaining device, a compressor and an aero-engine. Background Art

[0002] At present, in domestic and foreign aircraft engine compressors, in order to improve the margin of high-pressure compressors under all working conditions, the stator blades of the first few stages are usually designed as adjustable stator blades. The adjustable stator blades adjust the blade installation angle according to the working conditions during operation to ensure that the high-pressure compressor has sufficient margin, thereby ensuring the safe operation of the entire engine. Due to space limitations and ease of use and maintenance, the stator assembly where the adjustable stator is located is usually made into a split form, so that the inner ring of the adjustable stator blade is also set as a half-device form. The use of the half-device causes the following problems in the engineering implementation process:

[0003] 1) The adjustable stator blade (3) is composed of a blade body and a journal located at the upper and lower ends. The journal of the upper end of the adjustable stator blade is installed in the mounting hole of the outer support section of the casing, and the journal of the lower end is installed on the mounting hole of the inner ring (2). Since the inner ring adopts a split device, the upper and lower half rings of the inner ring are not constrained to each other and cannot be positioned, making it difficult to maintain its ideal design position. This unexpected spatial position change, on the one hand, makes it impossible for the rotating shafts of each adjustable stator blade in this stage to be evenly distributed, and thus causes a large difference in the circumferential adjustment accuracy of the adjustable stator blades of this stage. On the other hand, it will cause the adjustable stator blades of this stage to have an idle stroke at the extreme boundary of opening and closing, and thus cause a large difference in the realization of the same angle in the opening and closing process;

[0004] 2) Unexpected position changes of the inner ring are often manifested in the form of eccentricity of the inner ring, that is, one side of the inner ring will be higher than the flow channel, and the other side will be lower than the flow channel, thus creating forward and reverse steps in the flow channel, which will further affect the aerodynamic performance;

[0005] In summary, the air bleed demand results in a radial gap between the inner ring and the load-bearing casing. The radial gap causes unexpected changes in the spatial position of the inner ring of the inlet guide vane. This unexpected position change will cause poor adjustment accuracy of the inlet guide vane and forward and reverse steps in the flow channel, thereby affecting the aerodynamic performance. Summary of the invention

[0006] The technical problem to be solved by the present invention is to overcome the defects in the prior art and provide an inlet guide vane inner ring retaining device, a compressor and an aircraft engine.

[0007] The present invention solves the above technical problems through the following technical solutions:

[0008] An inlet guide vane inner ring retaining device comprises a casing and an inner ring; the inlet guide vane is mounted on the inner ring; at least a portion of one end of the inner ring facing the casing is mounted inside the casing; one of the casing and the inner ring is provided with a plurality of bosses arranged along the circumferential direction, and the other is provided with a plurality of grooves arranged along the circumferential direction; wherein the bosses and the grooves are respectively provided with a first working surface and a second working surface that cooperate with each other on both sides, and the first working surface and the second working surface are at an angle to the tangent line in the circumferential direction.

[0009] In the present technical solution, one of the casing and the inner ring is provided with a plurality of bosses arranged along the circumferential direction, and the other is provided with a plurality of grooves arranged along the circumferential direction, so that the bosses and the grooves cooperate with each other to achieve axial positioning of the casing and the inner ring, and the working surfaces of the bosses and the grooves that cooperate with each other form a certain angle with the tangent in the circumferential direction, so that resistance to eccentricity can be generated between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vanes and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vanes and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0010] Preferably, the first working surfaces on both sides of the boss are consistent in angle with the tangent line in the circumferential direction and are symmetrical with each other, and the second working surfaces on both sides of the groove are consistent in angle with the tangent line in the circumferential direction and are symmetrical with each other.

[0011] In the present technical solution, the symmetrical arrangement of the first working surface and the second working surface of the boss and the groove can not only ensure consistent eccentricity and balanced force, but also be more convenient and less costly in terms of processing and manufacturing compared to other irregular or asymmetric structures.

[0012] Preferably, the length of each boss in the circumferential direction is equal, and the plurality of bosses are evenly distributed in the circumferential direction; the length of each groove in the circumferential direction is equal, and the plurality of grooves are evenly distributed in the circumferential direction.

[0013] In the present technical solution, the bosses and grooves are of equal length in the circumferential direction and are evenly spaced in the circumferential direction, which is easy to install and disassemble and easy to process. In addition, the layout in which the bosses and grooves are of equal length and evenly spaced makes the working reliability high, and does not cause the defect of unreliable fixation due to local over-compactness or over-sparseness, and improves the aerodynamic performance of the high-pressure compressor to a certain extent.

[0014] Preferably, the boss is made of wear-resistant material.

[0015] In this technical solution, the boss is made of wear-resistant material to meet the compact and reliable assembly requirements, and prevent the boss from being worn due to mutual squeezing between the boss and the groove when eccentricity occurs, so that the subsequent calculation of the resistance to prevent eccentricity is accurate and effective.

[0016] Preferably, the inner ring comprises a first half ring and a second half ring which are spliced ​​together, the first half ring and the second half ring are provided with mounting holes in the circumferential direction, and the inner journal of the inlet guide vane is mounted on the first half ring and the second half ring through the mounting holes.

[0017] In this technical solution, an inner ring structure divided in half is adopted without the need to additionally set up a casing divided in half, which is suitable for the installation and positioning of a multifunctional integrated stator guide vane ring.

[0018] Preferably, when the first half ring or the second half ring has an eccentric tendency in any direction, the magnitude of the resistance generated by the mutual compression of the first working surface and the second working surface is:

[0019] Among them, f i is the resultant force of the mutual squeezing of the first working surface of the i-th boss and the second working surface of the groove; θ is the angle with the direction of the eccentricity trend; i is the first working surface and the second working surface of the i-th boss and the groove having an eccentricity trend.

[0020] In the present technical solution, when an eccentricity trend B occurs in any direction, there are always several positions in the circumferential direction where the first working surface and the second working surface in the boss and the groove squeeze each other to produce forces in opposite directions. The above formula can be used to calculate the squeezing forces between the first working surface and the second working surface of all the bosses and grooves to prevent the inner ring from being eccentric and maintain the working position of the inner ring.

[0021] Preferably, the boss and the groove are clearance-fitted.

[0022] In the present technical solution, the clearance fit between the boss and the groove can not only compensate for various errors, but also prevent the relative circumferential rotation of the casing and the inner ring while achieving axial positioning of the casing and the inner ring, thereby meeting the requirements of compact and reliable assembly. In addition, it can also facilitate the installation and disassembly of the casing and the inner ring.

[0023] Preferably, the maximum offset of the guide vane inner ring retaining device is:

[0024]

[0025] Among them, δ i is the gap between the boss and the groove, αi It is the angle between the first working surface of the boss and the second working surface of the groove and the eccentric trend direction.

[0026] In the present technical solution, the formula has a dual function. The first is to design the gap between the boss and the groove according to the above formula to calculate the maximum offset that occurs. The second is that due to processing deviations, the formula can be used to verify the maximum offset that exists.

[0027] The present invention also provides a compressor, comprising the inlet guide vane inner ring device described in any one of the above items, wherein the inlet guide vane is installed on the inlet guide vane inner ring device.

[0028] In the present technical solution, the compressor adopts the above-mentioned inlet guide inner ring device, which has the following advantages: by providing a plurality of bosses arranged along the circumferential direction on one of the casing and the inner ring, and providing a plurality of grooves arranged along the circumferential direction on the other, the bosses and the grooves cooperate with each other to achieve axial positioning of the casing and the inner ring, and the working surfaces of the bosses and the grooves that cooperate with each other are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vanes and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vanes, and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0029] The present invention also provides an aircraft engine, comprising the compressor described above.

[0030] In the present technical scheme, the aircraft engine adopts the above-mentioned inlet guide inner ring device, which has the following advantages: by providing a plurality of bosses arranged along the circumferential direction on one of the casing and the inner ring, and providing a plurality of grooves arranged along the circumferential direction on the other, the bosses and the grooves cooperate with each other to achieve axial positioning of the casing and the inner ring, and the working surfaces of the bosses and the grooves that cooperate with each other are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vanes and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vanes, and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0031] The positive and progressive effect of the present invention is that: by providing one of the casing and the inner ring with a plurality of bosses arranged along the circumferential direction, and the other with a plurality of grooves arranged along the circumferential direction, the bosses and the grooves cooperate with each other to achieve axial positioning of the casing and the inner ring, and the working surfaces of the bosses and the grooves that cooperate with each other form a certain angle with the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vanes during the test and the smoothness of the flow channel, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vanes, and improving the aerodynamic performance of the high-pressure compressor to a certain extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the structure of a conventional inlet guide vane inner ring device;

[0033] Figure 2 It is a schematic diagram of the three-dimensional structure of the casing in an embodiment of the present invention;

[0034] Figure 3 It is a schematic diagram of the structure of a part of the casing in an embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the three-dimensional structure of the inner ring in an embodiment of the present invention;

[0036] Figure 5 It is a schematic diagram of the structure of a part of the inner ring in an embodiment of the present invention;

[0037] Figure 6 It is a schematic diagram of the structure of the assembly of the casing and the inner ring in an embodiment of the present invention;

[0038] Figure 7 It is a cross-sectional schematic diagram of the assembly of the casing and the inner ring in an embodiment of the present invention;

[0039] Figure 8 It is a cross-sectional schematic diagram of a partial assembly section of a casing and an inner ring in an embodiment of the present invention;

[0040] Fig. 9 It is a schematic diagram of the clearance fit between the casing and the inner ring in an embodiment of the present invention.

[0041] Description of Reference Numerals :

[0042] Receiver 1

[0043] Inner Ring 2

[0044] Inlet guide vane 3

[0045] Boss 4

[0046] First working surface 41

[0047] Groove 5

[0048] Second working surface 51

[0049] Angle A

[0050] Eccentric trend in any direction B DETAILED DESCRIPTION

[0051] The present invention is further described below by way of examples, but the present invention is not limited to the scope of the examples.

[0052] like Figures 1 to 9As shown, this embodiment provides an inlet guide vane inner ring retaining device, including a casing 1 and an inner ring 2; the inlet guide vane 3 is installed on the inner ring 2; one of the casing 1 and the inner ring 2 is provided with a plurality of bosses 4 arranged along the circumferential direction, and the other is provided with a plurality of grooves 5 arranged along the circumferential direction; wherein, the bosses 4 and the grooves 5 are respectively provided with a first working surface 41 and a second working surface 51 that cooperate with each other on both sides, and the first working surface 41 and the second working surface 51 form an angle A with the tangent line in the circumferential direction.

[0053] By providing one of the casing 1 and the inner ring 2 with a plurality of bosses 4 arranged in the circumferential direction and the other with a plurality of grooves 5 arranged in the circumferential direction, the bosses 4 and the grooves 5 cooperate with each other to achieve axial positioning of the casing 1 and the inner ring 2, and the working surfaces of the bosses 4 and the grooves 5 that cooperate with each other form a certain angle with the tangent in the circumferential direction, so that resistance against eccentricity can be generated between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vane 3 during the test and the smoothness of the flow channel, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane 3 and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0054] It should be noted that, in this embodiment, there is no specific limitation on the angle between the first working surface 41 and the second working surface 51 and the tangent line in the axial direction, as long as the boss and the groove can cooperate with each other to achieve axial fixation of the casing and the inner ring.

[0055] In this embodiment, the first working surfaces 41 on both sides of the boss 4 are at the same angle as the tangent line in the circumferential direction and are symmetrical with each other, and the second working surfaces 51 on both sides of the groove 5 are at the same angle as the tangent line in the circumferential direction and are symmetrical with each other. In addition to making the eccentricity consistent and the force balanced, the symmetrical arrangement between the first working surface 41 and the second working surface 51 of the boss 4 and the groove 5 is more convenient to process and has lower cost than other irregular or asymmetric structures in terms of processing and manufacturing.

[0056] It should be noted that in other alternative embodiments, the first working surface 41 or the second working surface 51 on both sides can also be set to an irregular structure or an asymmetric structure, and can be adaptively adjusted according to actual needs, as long as the axial positioning of the casing 1 and the inner ring 2 can be achieved without affecting the aerodynamic performance. No specific limitation is made here.

[0057] In this embodiment, the lengths of the bosses 4 in the circumferential direction are equal, and the bosses 4 are evenly distributed in the circumferential direction; the lengths of the grooves 5 in the circumferential direction are equal, and the grooves 5 are evenly distributed in the circumferential direction. The bosses 4 and the grooves 5 are equal in length in the circumferential direction and evenly distributed in the circumferential direction, which is easy to install and disassemble, and easy to process. In addition, the layout of the bosses 4 and the grooves 5 with equal lengths and evenly distributed intervals makes the work reliability high, and there will be no defects of unreliable fixation due to local over-compactness or over-sparseness, and improves the aerodynamic performance of the high-pressure compressor to a certain extent.

[0058] It should be noted that in other alternative embodiments, bosses 4 and grooves 5 of different lengths and intervals may be provided according to actual needs, as long as the axial positioning of the casing 1 and the inner ring 2 can be achieved without affecting the aerodynamic performance, and no specific limitation is made here.

[0059] In this embodiment, the boss 4 is made of wear-resistant material. The boss 4 is made of wear-resistant material to meet the compact and reliable assembly requirements, and prevent the boss 4 from being worn due to mutual compression between the boss 4 and the groove 5 when an eccentricity tendency occurs, so that the result of subsequent calculation of the resistance to prevent the eccentricity tendency is accurate and effective.

[0060] Specifically, the wear-resistant material can be: for example, chromium carbide, high manganese steel, tungsten carbide, etc. It should be noted that the material used for the boss 4 is not limited to the above materials. As long as the boss 4 and the groove 5 can be prevented from being squeezed against each other and causing wear of the boss 4 when an eccentricity tendency occurs, no specific limitation is made here.

[0061] In this embodiment, the inner ring 2 is a first half ring and a second half ring (not shown in the figure) that are spliced ​​and evenly divided in half. The first half ring and the second half ring are fixed by welding or bolting, which is not specifically limited here. The first half ring and the second half ring are provided with mounting holes in the circumferential direction, and the inner journal of the inlet guide vane 3 is mounted on the first half ring and the second half ring through the mounting holes. The half-split inner ring 2 structure is adopted without the need to additionally set up a half-split casing 1, which is suitable for the installation and positioning of the multifunctional integrated stator guide vane ring.

[0062] It should be noted that in other alternative embodiments, the inner ring 2 may also be a full ring or composed of 3 or 4 equally or unequally divided rings, and may be adaptively adjusted according to actual needs, which is not specifically limited here.

[0063] Combination Figures 8 to 9 When the first half ring or the second half ring has an eccentricity trend B in any direction, the resistance generated by the first working surface 41 and the second working surface 51 squeezing each other is:

[0064] It should be emphasized that for a certain boss 4 or groove, f i is the resultant force of the mutual squeezing force between the first working surface 41 and the second working surface 51; θ is the angle with the eccentricity trend direction; i is the first working surface 41 and the second working surface 51 of the i-th boss 4 and the groove 5 with the eccentricity trend. . When the eccentricity trend B occurs in any direction, there are always several bosses in the circumferential direction that squeeze and generate opposite direction forces between the first working surface 41 and the second working surface 51 in the groove. The above formula can be used to calculate the squeezing force between the first working surface 41 and the second working surface 51 of all bosses and grooves to prevent the inner ring 2 from eccentricity and maintain the working position of the inner ring 2.

[0065] In this embodiment, the boss 4 and the groove 5 are clearance-fitted. In addition to compensating for various errors, the clearance-fitted between the boss 4 and the groove 5 can also prevent the casing 1 and the inner ring 2 from rotating relative to each other in the circumferential direction while realizing the axial positioning of the casing 1 and the inner ring 2, thereby meeting the compact and reliable assembly requirements, and also facilitating the installation and removal of the casing 1 and the inner ring 2.

[0066] In this embodiment, the maximum offset of the retaining device of the inner ring 2 of the guide vane, the gap δ between the boss 4 and the groove 5 i and the angle α between the first working surface 41 of the boss 4 and the second working surface 51 of the groove 5 and the eccentricity trend direction i The relationship between the three satisfies the following formula:

[0067]

[0068] In this embodiment, the boss 4 and the groove 5 are clearance-matched, so the gap δ between the boss 3 and the groove 5 is i is a known quantity, and the angle between the first working surface 41 and the second working surface 51 is also a known quantity. Therefore, the maximum offset L can be verified according to the formula. It should be noted that in other alternative embodiments, when the maximum offset L is known, the angle α between the first working surface 41 and the second working surface 45 and the circumferential direction is i In the case of , the gap δ between the boss 4 and the groove can also be designed by the above formula i Or, the gap δ between the known boss 4 and the groove 5 i , when the maximum offset L is reached, the angle between the first working surface 41 and the second working surface 51 and the circumferential direction can also be calculated by the above formula.

[0069] Example 2

[0070] This embodiment provides a compressor, including the inlet guide vane inner ring device described in Embodiment 1, wherein the inlet guide vane 3 is installed on the inlet guide vane inner ring device.

[0071] The compressor adopts the above-mentioned inlet guide vane inner ring device, which has the following advantages: by providing a plurality of bosses 4 arranged along the circumferential direction on one of the casing 1 and the inner ring 2, and providing a plurality of grooves 5 arranged along the circumferential direction on the other, the bosses 4 and the grooves 5 cooperate with each other to achieve axial positioning of the casing 1 and the inner ring 2, and the working surfaces of the bosses 4 and the grooves 5 that cooperate with each other form a certain angle with the tangent in the circumferential direction, so that resistance against eccentricity can be generated between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vane 3 during the test and the smoothness of the flow channel, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane 3, and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0072] Example 3

[0073] This embodiment provides an aircraft engine, including the compressor described in Embodiment 2. The advantages of using the inlet guide vane inner ring retaining device of Embodiment 1 are not described in detail here, please refer to the description in Embodiment 1 or Embodiment 2.

[0074] In summary, by providing a plurality of bosses 4 arranged along the circumferential direction on one of the casing 1 and the inner ring 2, and providing a plurality of grooves 5 arranged along the circumferential direction on the other, the bosses 4 and the grooves 5 cooperate with each other to achieve axial positioning of the casing 1 and the inner ring 2, and the working surfaces of the bosses 4 and the grooves 5 that cooperate with each other form a certain angle with the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces, effectively improving the adjustment accuracy of the inlet guide vane 3 and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane 3, and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0075] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that this is only for illustration and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. An inlet guide vane inner ring retaining device, characterized in that: It comprises a casing and an inner ring; the inlet guide vane is mounted on the inner ring; at least a portion of one end of the inner ring facing the casing is mounted inside the casing; One of the casing and the inner ring is provided with a plurality of bosses arranged in the circumferential direction, and the other is provided with a plurality of grooves arranged in the circumferential direction; Wherein, the two sides of the boss and the groove are respectively provided with a first working surface and a second working surface that match each other, and the first working surface and the second working surface form an angle with the tangent line in the circumferential direction.

2. The inlet guide vane inner ring retaining device according to claim 1, characterized in that: The first working surfaces on both sides of the boss are consistent in angle with the tangent line in the circumferential direction and are symmetrical with each other. The second working surfaces on both sides of the groove are consistent in angle with the tangent line in the circumferential direction and are symmetrical with each other.

3. The inlet guide vane inner ring retaining device according to claim 1, characterized in that: The lengths of the bosses in the circumferential direction are all equal, and the multiple bosses are evenly distributed in the circumferential direction; the lengths of the grooves in the circumferential direction are all equal, and the multiple grooves are evenly distributed in the circumferential direction.

4. The inlet guide vane inner ring retaining device according to claim 1, wherein the boss is made of wear-resistant material.

5. The inlet guide vane inner ring retaining device according to claim 1, characterized in that: The inner ring comprises a first half ring and a second half ring which are spliced ​​together, the first half ring and the second half ring are provided with mounting holes in the circumferential direction, and the inner journal of the inlet guide vane is mounted on the first half ring and the second half ring through the mounting holes.

6. The inlet guide vane inner ring retaining device according to claim 5, characterized in that: When the first half ring or the second half ring has an eccentricity tendency in any direction, the resistance generated by the mutual compression of the first working surface and the second working surface is: Among them, f i is the resultant force of the mutual extrusion between the first working surface of the ith boss and the second working surface of the groove; θ is f i The angle with the direction of the eccentricity trend; i is the first working surface and the second working surface of the boss and the groove where the eccentricity trend occurs for the i-th time.

7. The inlet guide vane inner ring retaining device according to claim 1, characterized in that: The boss and the groove are clearance-matched.

8. The inlet guide vane inner ring retaining device according to claim 7, characterized in that: The maximum offset of the guide vane inner ring retaining device is: Among them, δ i is the gap between the boss and the groove, α i It is the angle between the first working surface of the boss and the second working surface of the groove and the eccentricity trend direction.

9. A compressor, characterized in that: It comprises the inlet guide vane inner ring device according to any one of claims 1 to 8, and the inlet guide vane is installed on the inlet guide vane inner ring device.

10. An aircraft engine, characterized in that: Comprising the compressor as claimed in claim 9.

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