Inlet guide vane inner ring retaining device, compressor and aeroengine

Abstract

The application discloses an inlet guide vane inner ring retaining device, a compressor and an aero-engine. The inlet guide vane inner ring retaining device comprises a casing and an inner ring. At least a part of the end of the inner ring facing the casing is mounted in the interior of 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 in the circumferential direction, and the other is provided with a plurality of grooves arranged in the circumferential direction. The two sides of the boss and the groove are respectively provided with a first working surface and a second working surface matched with each other, and the two working surfaces are both at an angle with the tangent of the circumferential direction. Through the above technical scheme, the axial positioning of the casing and the inner ring can be realized, the resistance between the working surfaces resisting eccentricity can be generated, the adjustment accuracy of the inlet guide vane in the test process and the smoothness of the flow channel can be effectively improved, the consistency of the aerodynamic performance of the inlet guide vane is ensured, and the aerodynamic performance of the high-pressure compressor is improved to some extent.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine guide vane adjustment technology, and particularly relates to an inlet guide vane inner ring retaining device, a compressor, and an aero-engine. Background Technology

[0002] Currently, in domestic and international aero-engine compressors, to improve the margin of high-pressure compressors across all operating conditions, the first few stages of stator blades are typically designed as adjustable stator blades. These adjustable stator blades adjust their installation angle according to operating conditions to ensure sufficient margin in the high-pressure compressor, thereby guaranteeing the safe operation of the entire engine. Due to space constraints and ease of use and maintenance, the stator assembly containing the adjustable stator is usually designed in a split configuration, meaning the inner ring of the adjustable stator blades is also configured as a half-and-half device. The use of this half-and-half device presents the following problems in engineering implementation:

[0003] 1) The adjustable stator blade (3) consists of a blade body and journals 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 in the mounting hole of the inner ring (2). Since the inner ring adopts a split device, the upper and lower halves of the inner ring are not constrained to each other, cannot be positioned, and are difficult to maintain their ideal design position. This unexpected change in spatial position makes it impossible for the rotating shafts of each adjustable stator blade in this stage to be evenly distributed, which in turn makes the adjustment accuracy of the adjustable stator blade in this stage circumferentially different. On the other hand, it will cause the adjustable stator blade in this stage to have empty stroke at the limit boundary of opening and closing, which in turn makes the same angle achieved in the opening and closing process significantly different.

[0004] 2) Unexpected changes in the position of the inner ring often manifest as an eccentric inner ring, where one side of the inner ring is higher than the flow channel and the other side is lower than the flow channel. This creates a forward and reverse step in the flow channel, which will further affect the aerodynamic performance.

[0005] In summary, the bleed air requirement results in a radial clearance between the inner ring and the load-bearing casing. This radial clearance causes an unexpected change in the spatial position of the inner ring of the inlet guide vane. This unexpected change in position will lead to poor adjustment accuracy of the inlet guide vane and the formation of forward and reverse steps in the flow channel, thereby affecting 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 aero engine.

[0007] The present invention solves the above-mentioned technical problems through the following technical solution:

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

[0009] In this technical solution, multiple bosses are provided in one of the casing and inner ring along the circumferential direction, and multiple grooves are provided in the other along the circumferential direction. The bosses and grooves cooperate with each other to achieve axial positioning of the casing and inner ring. Furthermore, the working surfaces of the bosses and grooves are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces. This effectively improves the adjustment accuracy of the inlet guide vane and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane 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 at the same angle to the tangent in the circumferential direction and are symmetrical to each other, and the second working surfaces on both sides of the groove are at the same angle to the tangent in the circumferential direction and are symmetrical to each other.

[0011] In this technical solution, the symmetrical arrangement of the first and second working surfaces of the boss and the groove not only ensures consistent eccentricity and balanced force, but also makes the processing and manufacturing process easier and cheaper compared to other irregular or asymmetrical structures.

[0012] Preferably, the lengths of each of the bosses in the circumferential direction are equal, and the plurality of bosses are evenly distributed in the circumferential direction; the lengths of each of the grooves in the circumferential direction are equal, and the plurality of grooves are evenly distributed at intervals in the circumferential direction.

[0013] In this technical solution, the bosses and grooves are of equal length in the circumferential direction and are evenly distributed in the circumferential direction, which makes them easy to install and disassemble and easy to process. In addition, the layout of equal length and evenly distributed bosses and grooves ensures high reliability and avoids defects such as unreliable fixation due to excessive compactness or sparseness in some areas, and improves the aerodynamic performance of the high-pressure compressor to a certain extent.

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

[0015] In this technical solution, the boss is made of a wear-resistant material, which can meet the requirements of compact and reliable assembly, and prevent the boss from being squeezed against the groove when eccentricity occurs, thus preventing the boss from wearing. This makes the results accurate and effective when calculating the resistance to prevent eccentricity in subsequent calculations.

[0016] Preferably, the inner ring includes a first half-ring and a second half-ring that are spliced ​​together, and the first half-ring and the second half-ring are provided with mounting holes in the circumferential direction. 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] This technical solution adopts a bi-half-divided inner ring structure, eliminating the need for an additional bi-half-divided casing, and is suitable for the installation and positioning of multi-functional integrated stator guide vane rings.

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

[0019] Among them, f i θ is the resultant force of the mutual pressing force between 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 that exhibit the eccentricity trend.

[0020] In this technical solution, when an eccentric tendency B occurs in any direction, there are always several protrusions in the circumferential direction that exert opposite forces on the first and second working surfaces in the groove. The above formula can be used to calculate the forces exerted on the first and second working surfaces of all protrusions and grooves to prevent the inner ring from becoming eccentric and to maintain the working position of the inner ring.

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

[0022] In this 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. This can meet the requirements of compact and reliable assembly. In addition, it can 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] Where, δ i α is the gap between the boss and the groove.i The angle between the first working surface of the boss and the second working surface of the groove and the eccentricity trend direction.

[0026] In this technical solution, the formula has a dual function. The first function is to design the gap between the boss and the groove according to the above formula in order to calculate the maximum offset. The second function is that, since there are deviations in the processing, the maximum offset can be verified according to the formula.

[0027] The present invention also provides a compressor comprising the inlet guide vane inner ring device as described in any of the preceding claims, wherein the inlet guide vane is mounted on the inlet guide vane inner ring device.

[0028] In this technical solution, the compressor adopts the aforementioned inlet guide ring device, which has the following advantages: by providing multiple bosses arranged circumferentially on one of the casing and the inner ring, and multiple grooves arranged circumferentially on the other, the bosses and grooves cooperate to achieve axial positioning of the casing and the inner ring. Furthermore, the working surfaces of the bosses and grooves 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 vane and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

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

[0030] In this technical solution, the aero-engine adopts the aforementioned inlet guide ring device, which has the following advantages: by providing multiple bosses arranged circumferentially on one of the casing and the inner ring, and multiple grooves arranged circumferentially on the other, the bosses and grooves cooperate to achieve axial positioning of the casing and the inner ring. Furthermore, the working surfaces of the bosses and grooves 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 vane and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane and improving the aerodynamic performance of the high-pressure compressor to a certain extent.

[0031] The positive and progressive effects of this invention are as follows: by providing multiple bosses arranged circumferentially on one of the casing and the inner ring, and multiple grooves arranged circumferentially on the other, the bosses and grooves cooperate to achieve axial positioning of the casing and the inner ring. Furthermore, the working surfaces of the bosses and grooves are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces. This effectively improves the adjustment accuracy of the inlet guide vane and the smoothness of the flow channel during the test, thereby ensuring the consistency of the aerodynamic performance of the inlet guide vane and improving the aerodynamic performance of the high-pressure compressor to a certain extent. Attached Figure Description

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

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

[0034] Figure 3 This is a partial structural diagram of the casing in an embodiment of the present invention;

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

[0036] Figure 5 This is a schematic diagram of a portion of the inner ring in an embodiment of the present invention;

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

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

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

[0041] Explanation of reference numerals in the attached figures :

[0042] Casing 1

[0043] Inner Ring 2

[0044] Imported guide vanes 3

[0045] Boss 4

[0046] First working face 41

[0047] Groove 5

[0048] Second working face 51

[0049] Angle A

[0050] Eccentricity trend B in any direction Detailed Implementation

[0051] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments described herein.

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

[0053] By providing multiple bosses 4 arranged circumferentially on one of the casing 1 and the inner ring 2, and multiple grooves 5 arranged circumferentially on the other, the bosses 4 and grooves 5 cooperate to achieve axial positioning of the casing 1 and the inner ring 2. Furthermore, the working surfaces of the bosses 4 and grooves 5 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. This effectively improves 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.

[0054] It should be noted that in this embodiment, the angle between the first working surface 41 and the second working surface 51 and the tangent in the axial direction is not specifically limited, 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 to the tangent in the circumferential direction and are symmetrical with respect to each other. Similarly, the second working surfaces 51 on both sides of the groove 5 are at the same angle to the tangent in the circumferential direction and are symmetrical with respect to each other. The symmetrical arrangement of the first working surfaces 41 and second working surfaces 51 of the boss 4 and the groove 5 not only ensures consistent eccentricity and balanced force distribution, but also makes manufacturing easier and less costly compared to other irregular or asymmetrical structures.

[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 as an irregular structure or an asymmetrical structure. Adaptive adjustments can be made 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 each boss 4 in the circumferential direction are equal, and the multiple bosses 4 are evenly distributed in the circumferential direction; the lengths of each groove 5 in the circumferential direction are equal, and the multiple grooves 5 are evenly spaced in the circumferential direction. The equal lengths of the bosses 4 and grooves 5 in the circumferential direction and their evenly spaced distribution facilitate installation and disassembly, and are easy to manufacture. Furthermore, the layout of equal lengths and evenly spaced grooves 4 and 5 ensures high operational reliability, preventing defects such as unreliable fixation due to excessively tight or sparse areas, and to a certain extent improves the aerodynamic performance of the high-pressure compressor.

[0058] It should be noted that in other alternative embodiments, bosses 4 and grooves 5 with different lengths and intervals can also be set 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.

[0059] In this embodiment, the boss 4 is made of a wear-resistant material. Using a wear-resistant material for the boss 4 meets the requirements for compact and reliable assembly, and prevents the boss 4 from wearing due to mutual compression between the boss 4 and the groove 5 in the event of eccentricity. This ensures accurate and effective results in subsequent calculations of the resistance to prevent eccentricity.

[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 it can prevent the boss 4 and the groove 5 from squeezing each other and causing the boss 4 to wear when there is an eccentric tendency, it is acceptable. No specific limitation is made here.

[0061] In this embodiment, the inner ring 2 consists of a first half-ring and a second half-ring (not shown in the figure) that are spliced ​​together and equally divided. The first half-ring and the second half-ring are fixed by welding or bolting, etc., without specific limitations. Mounting holes are provided in the circumferential direction of the first half-ring and the second half-ring, 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. This equally divided inner ring 2 structure eliminates the need for an additional equally divided casing 1, making it suitable for the installation and positioning of multi-functional integrated stator guide vane rings.

[0062] It should be noted that in other alternative embodiments, the inner ring 2 can also be a whole ring or composed of 3 or 4 equally or unevenly divided rings. Adaptive adjustments can be made according to actual needs, and no specific limitation is made here.

[0063] Combination Figures 8 to 9 When the first or second half-ring exhibits an eccentric tendency B in any direction, the magnitude of the resistance generated by the mutual compression of the first working surface 41 and the second working surface 51 is:

[0064] It is important to emphasize that, for a specific boss 4 or groove, f i The resultant force of the mutual pressing force between the first working surface 41 and the second working surface 51 is given by formula B; θ is the angle with the direction of the eccentric tendency; i represents the first working surface 41 and the second working surface 51 of the i-th boss 4 and groove 5 that exhibit eccentric tendency. When an eccentric tendency B occurs in any direction, there are always several positions of bosses in the circumferential direction that exert opposing forces on the first working surface 41 and the second working surface 51 in the groove. The above formula can be used to calculate the pressing 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 becoming eccentric and to maintain the working position of the inner ring 2.

[0065] In this embodiment, the boss 4 and the groove 5 are fitted with a clearance fit. In addition to compensating for various errors, the clearance fit between the boss 4 and the groove 5 can also prevent the relative circumferential rotation of the casing 1 and the inner ring 2 while achieving axial positioning of the casing 1 and the inner ring 2. This can meet the requirements of compact and reliable assembly. Furthermore, it can facilitate the installation and disassembly of the casing 1 and the inner ring 2.

[0066] In this embodiment, the maximum offset of the guide vane inner ring 2 retaining device and the gap δ between the boss 4 and the groove 5 are... 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 fitted with a clearance, therefore the clearance δ between the boss 3 and the groove 5 is... i Since the angle between the first working surface 41 and the second working surface 51 is also known, the maximum offset L can be verified using this formula. It should be noted that in other alternative embodiments, the known maximum offset L, the angle α between the first working surface 41 and the second working surface 45 and the circumferential direction, and other factors are also known. i In this case, the gap δ between the boss 4 and the groove can also be designed using the above formula. i Alternatively, the known gap δ between the boss 4 and the groove 5. i In the case of the maximum offset L, the angle between the first working surface 41 and the second working surface 51 and the circumferential direction can also be calculated using 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 employs the aforementioned inlet guide vane inner ring device, which has the following advantages: By providing multiple protrusions 4 arranged circumferentially on one of the casing 1 and the inner ring 2, and multiple grooves 5 arranged circumferentially on the other, the protrusions 4 and grooves 5 cooperate to achieve axial positioning of the casing 1 and the inner ring 2. Furthermore, the working surfaces of the protrusions 4 and grooves 5 are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces. This effectively improves 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.

[0072] Example 3

[0073] This embodiment provides an aero-engine, including the compressor described in Embodiment 2. The advantages of using the inlet guide vane inner ring retaining device of Embodiment 1 will not be elaborated here; please refer to the descriptions in Embodiment 1 or Embodiment 2.

[0074] In summary, by providing multiple bosses 4 arranged circumferentially on one of the casing 1 and the inner ring 2, and multiple grooves 5 arranged circumferentially on the other, the bosses 4 and grooves 5 cooperate to achieve axial positioning of the casing 1 and the inner ring 2. Furthermore, the working surfaces of the bosses 4 and grooves 5 are at a certain angle to the tangent in the circumferential direction, which can generate resistance against eccentricity between the working surfaces. This effectively improves 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] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. An inlet guide vane inner ring retaining device, characterized in that, It includes a casing and an inner ring; an inlet guide vane is mounted on the inner ring; at least a portion of the inner ring facing the casing is installed 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. The boss and the groove are respectively provided with a first working surface and a second working surface that cooperate with each other, and the first working surface and the second working surface are at an angle to the tangent in the circumferential direction. The boss and the groove are fitted with a clearance. The maximum offset of the guide vane inner ring retaining device is: Where, δ i α is the gap between the boss and the groove. i The angle between the first working surface of the boss and the second working surface of the groove and the eccentricity trend direction.

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

3. The inlet guide vane inner ring retaining device as described in claim 1, characterized in that, The lengths of each of the bosses in the circumferential direction are equal, and the bosses are evenly distributed in the circumferential direction; the lengths of each of the grooves in the circumferential direction are equal, and the grooves are evenly distributed at intervals in the circumferential direction.

4. The inlet guide vane inner ring retaining device as described in claim 1, wherein the boss is made of a wear-resistant material.

5. The inlet guide vane inner ring retaining device as described in claim 1, characterized in that, The inner ring includes a first half-ring and a second half-ring that are spliced ​​together. The first half-ring and the second half-ring have mounting holes in their circumferential direction. 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 as described in claim 5, characterized in that, When the first or second half-ring exhibits an eccentric tendency in any direction, the magnitude of the resistance generated by the mutual compression of the first and second working surfaces is: Among them, f i θ is the resultant force of the mutual pressing force between the first working surface of the i-th boss and the second working surface of the groove; f is i The angle between the eccentricity trend direction and the first working surface and the second working surface of the i-th boss and groove that exhibit the eccentricity trend.

7. A compressor, characterized in that, Includes the inlet guide vane inner ring retaining device as described in any one of claims 1-6, wherein the inlet guide vane is mounted on the inlet guide vane inner ring retaining device.

8. An aircraft engine, characterized in that, Includes the compressor as described in claim 7.

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