A composite functional compressor casing with a gas collecting cavity structure

Abstract

A composite functional compressor casing with a gas collecting cavity structure, comprising a casing body, and an annular casing composed of a first cavity outer shell and a second cavity outer shell; two annular cavities are arranged on the circumferential surface of the casing body; the first cavity outer shell covers one of the annular cavities to form a first annular gas collecting cavity; the second cavity outer shell covers the other annular cavity to form a second annular gas collecting cavity; a first cavity air extraction hole is arranged on the first cavity outer shell; a second cavity air extraction hole is arranged on the second cavity outer shell; two groups of positioning pin lugs are arranged on the annular casing, the two groups of positioning pin lugs are longitudinally arranged at an interval of 180°, and each group is provided with a plurality of positioning pin lugs; positioning pin through holes are arranged at positions on the inner side wall of the casing body opposite to each positioning pin lug; a plurality of observation window lugs are arranged on the annular casing; a first gas collecting cavity ventilation hole is arranged on the inner side wall of the casing body and communicated with the first annular gas collecting cavity, and a second gas collecting cavity ventilation hole is arranged and communicated with the second annular gas collecting cavity.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine compressor casings, and particularly to a composite functional compressor casing with a gas collecting cavity structure. Background Art

[0002] The compressor casing is one of the important parts of an aero-engine. It is the base of the entire engine and one of the main load-bearing shells of the engine. During operation, it bears various loads such as torque, axial force, bending moment transmitted from adjacent components, as well as thermal load and vibration load. At the same time, it is the geometric outer wall of the air flow channel and one of the important carriers for realizing the aerodynamic performance of the engine. According to its structure and working characteristics, the general design requirements for aero-engine compressor casings are light weight, high strength, and high stiffness, capable of withstanding various loads and the deformation of the casing within the allowable range. This is also the main guiding principle and criterion for the current design of compressor casings, and a large number of related studies have been carried out by scholars at home and abroad. However, with the development of aero-engine design technology and the refinement of functional requirements, the functional requirements for compressor casings are also diversified, the structural design is more complex, and the design of composite functional compressor casings is becoming increasingly important. Summary of the Invention

[0003] The main object of the present invention is to propose a composite functional compressor casing with a gas collecting cavity structure to solve the design problem of a compressor casing with an air extraction requirement, and at the same time take into account the easy installation and detectable function design of the compressor casing.

[0004] To achieve the above object, the present invention proposes a composite functional compressor casing with a gas collecting cavity structure, including a casing shell and an annular casing composed of a first cavity outer shell and a second cavity outer shell; two annular cavities are provided on the circumferential surface of the casing shell; the first cavity outer shell covers one of the annular cavities to form a first annular gas collecting cavity; the second cavity outer shell covers the other annular cavity to form a second annular gas collecting cavity; a first cavity air extraction hole is provided on the first cavity outer shell; a second cavity air extraction hole is provided on the second cavity outer shell; two groups of positioning pin lugs are provided on the annular casing, and the two groups of positioning pin lugs are longitudinally arranged 180° apart, and each group is provided with a plurality of positioning pin lugs; positioning pin through holes are provided on the inner side wall of the casing shell at positions opposite to each positioning pin lug; a plurality of observation window lugs are provided on the annular casing; a first gas collecting cavity ventilation hole is provided on the inner side wall of the casing shell and communicated with the first annular gas collecting cavity, and a second gas collecting cavity ventilation hole is provided and communicated with the second annular gas collecting cavity.

[0005] Preferably, a lock bottom structure is provided on the casing shell, and the first cavity outer shell and the second cavity outer shell are respectively lapped on the lock. Preferably, a first cavity air extraction mounting seat is welded at the first cavity air extraction hole; a second cavity air extraction mounting seat is welded at the second cavity air extraction hole.

[0006] Preferably, the positioning pin lug and the observation window lug are both fixed on the annular casing by welding. After welding, the positioning pin lug and the observation window lug are drilled by a combined machining method, and all the drilled holes are through holes.

[0007] Preferably, eight pins are evenly distributed in a ring on the inner surface of the rear end of the casing. The pins are fixed on the inner surface of the rear end of the casing by flaring; the pins are used to cooperate with the "U"-shaped grooves on the engine fairing window to fix the circumferential position of the fairing window.

[0008] Preferably, a front mounting edge is provided at the front end of the casing, and a rear mounting edge is provided at the rear end; front mounting holes are provided on the front mounting edge, and rear mounting holes are provided on the rear mounting edge.

[0009] Preferably, in each group of positioning pin lugs, the number of positioning pin lugs is six.

[0010] Preferably, the number of air extraction holes on the outer shell of the first chamber is three

[0011] Preferably, the number of air extraction holes on the outer shell of the second chamber is two.

[0012] Preferably, the number of observation window lugs is three, and the three observation window lugs are arranged longitudinally.

[0013] Due to the adoption of the above technical solutions, the beneficial effects of the present invention are as follows:

[0014] The present invention adopts an integral ring casing structure composed of a casing, a first chamber outer shell, and a second chamber outer shell, with uniform stiffness distribution and uniform rigidity at each position. Compared with a split casing, the roundness of the casing is easier to maintain; the setting of the first annular air collecting chamber and the second annular air collecting chamber solves the problems of turbine cooling and aircraft cockpit air conditioning air extraction. The air collecting chamber structure strengthens the stability and continuity during air extraction, and at the same time, the double-layer ring cavity structure enhances the strength and stiffness of the annular casing; two groups of longitudinally arranged positioning pin lugs are arranged outside the annular casing, which can be matched with positioning pins to simultaneously position the circumferential positions of multiple stages of rectifiers from front to back. The structure is simple and efficient, and there is also an obvious weight reduction effect compared with the usual method of fixing rectifiers with bolts; multiple observation window lugs are provided to meet the daily detectability and maintainability functions of the compressor; the structure of the present invention is simple, the processing cost is low, the strength and rigidity of the casing are high, and it takes into account functions such as air extraction, installation positioning, detectability and maintenance, and has good application prospects and high economic benefits. Description of the Drawings

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0016] Figure 1 It is a structural sectional view of the present invention;

[0017] Figure 2 It is an installation schematic diagram of the air extraction mounting seat, air extraction hole and observation window lug in the present invention;

[0018] Figure 3 It is a structural schematic diagram of the casing housing in the present invention;

[0019] Figure 4 It is a structural schematic diagram of the front mounting edge of the casing housing in the present invention;

[0020] Figure 5 It is a structural schematic diagram of the rear mounting edge of the casing housing in the present invention;

[0021] Figure 6 It is a schematic diagram of the connection between the compressor casing, turbine air duct and cockpit air duct provided by the present invention;

[0022] Figure 7 It is a schematic diagram of the connection between the compressor casing and the rectifier through the positioning pin provided by the present invention;

[0023] Figure 8 It is a schematic diagram of the upper diversion window and its "U" - shaped groove on the engine;

[0024] Figure 9 It is a schematic diagram of the connection between the front mounting edge of the casing housing and the first casing in the present invention;

[0025] Figure 10 It is a schematic diagram of the connection between the rear mounting edge of the casing housing and the diffuser in the present invention;

[0026] Figure 11 It is a schematic diagram of the observation window plug.

[0027] Description of the reference numerals in the drawings: 1. Ring-shaped casing; 2. Casing housing; 201. Pin through-hole; 3. Outer shell of the first chamber; 4. Outer shell of the second chamber; 5. Air extraction mounting seat of the first chamber; 6. Air extraction mounting seat of the second chamber; 7. Pin lug; 8. Observation window lug; 9. Pin; 10. First annular air collection chamber; 11. Second annular air collection chamber; 12. Front mounting hole; 13. Rear mounting hole; 14. First bolt; 15. Washer; 16. Second bolt; 17. Adjusting ring; 18. Nut; 19. First casing; 20. Diffuser; 21. Bottom locking structure; 22. Vent hole of the first air collection chamber; 23. Vent hole of the second air collection chamber; 24. Air extraction hole of the first chamber; 25. Air extraction hole of the second chamber; 26. Turbine air duct; 27. Cockpit air duct; 28. Positioning pin; 29. 6-stage rectifier; 30. Deflector window; 31. "U"-shaped groove; 32. Observation window plug. Detailed implementation manners

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0029] It should be noted that all the directional indications (such as up, down, left, right, front, rear...) in the embodiments of the present invention are only used to explain the relative positional relationship and movement conditions between components in a specific posture (as shown in the accompanying drawings). If this specific posture changes, the directional indications will also change accordingly.

[0030] In addition, the descriptions involving "first", "second", etc. in the present invention are only for descriptive purposes, and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the fact that those of ordinary skill in the art can implement them. When the combination of technical solutions appears to be contradictory or unable to be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present invention.

[0031] Combined with Figures 1 to 3 As shown, a composite function compressor casing with an air collection chamber structure is characterized by comprising a casing housing 2 and a ring-shaped casing 1 composed of an outer shell 3 of the first chamber and an outer shell 4 of the second chamber;

[0032] There are two annular cavities arranged on the circumferential surface of the casing 2; the casing 2 is formed by machining a forging, and the outer shell 3 of the first cavity and the outer shell 4 of the second cavity are formed by bending plates.

[0033] The outer shell 3 of the first cavity covers one of the annular cavities to form the first annular gas collecting cavity 10; the outer shell 4 of the second cavity covers the other annular cavity to form the second annular gas collecting cavity 11;

[0034] There is a first cavity air extraction hole 24 arranged on the outer shell 3 of the first cavity; there is a second cavity air extraction hole 25 arranged on the outer shell 4 of the second cavity; a first cavity air extraction mounting seat 5 is welded at the first cavity air extraction hole 24; a second cavity air extraction mounting seat 6 is welded at the second cavity air extraction hole 25. Connecting by welding is beneficial to ensuring the sealing performance of the connection part.

[0035] There are two groups of positioning pin lugs 7 arranged on the annular casing 1. The two groups of positioning pin lugs 7 are longitudinally arranged 180° apart, and each group has six positioning pin lugs 7; positioning pin through holes 201 are arranged at the positions opposite to each positioning pin lug 7 on the inner side wall of the casing 2;

[0036] There are multiple observation window lugs 8 arranged on the annular casing 1;

[0037] First cavity gas collecting cavity vent holes 22 are uniformly arranged on the inner side wall of the casing 2 and communicate with the first annular gas collecting cavity 10, and second cavity gas collecting cavity vent holes 23 are uniformly arranged and communicate with the second annular gas collecting cavity 11.

[0038] Combined Figure 3 As shown, a bottom locking structure 21 is arranged on the casing 2. The cross-section of the bottom locking structure 21 is a concave rabbet structure. The outer shell 3 of the first cavity and the outer shell 4 of the second cavity are respectively lapped on the bottom locking structure 21 and welded to the casing 2.

[0039] Combined Figure 1 、 Figure 2 As shown, the positioning pin lugs 7 and the observation window lugs 8 are both fixed on the annular casing 1 by welding. After welding, the positioning pin lugs 7 and the observation window lugs 8 are drilled by a combined machining method, and the drilled holes are all through holes.

[0040] Combined Figure 1 、 Figure 8 As shown, eight pins 9 are annularly and uniformly arranged on the inner surface of the rear end of the casing 2. The pins 9 are fixed on the inner surface of the rear end of the casing 2 by flaring; the pins 9 are used to cooperate with the "U"-shaped grooves on the engine deflector window to fix the circumferential position of the deflector window.

[0041] Combined Figure 4 、 Figure 5As shown, a front mounting flange is provided at the front end of the casing housing 2, and a rear mounting flange is provided at the rear end; a front mounting hole 12 is provided on the front mounting flange, and a rear mounting hole 13 is provided on the rear mounting flange.

[0042] In this embodiment, the number of the first chamber extraction holes 24 provided on the first chamber housing 3 is three, and the number of the second chamber extraction holes 25 provided on the second chamber housing 4 is two. The number of the observation window lugs 8 is three, and the three observation window lugs 8 are arranged longitudinally.

[0043] The working principle of the present invention is as follows:

[0044] Combined with Figure 9 、 Figure 10 、and Figure 6 、 Figure 7 As shown, during assembly, the front mounting flange of the casing housing 2 is connected to the first casing 19 through the first bolt 14 and the washer 15, and the rear mounting flange is connected to the diffuser 20 through the second bolt 16, the adjusting ring 17, and the nut 18. The three first chamber extraction mounts 5 are connected to the turbine air duct 26, and the two second chamber extraction mounts 6 are connected to the cockpit air duct 27. After the air flow enters the first annular air collecting chamber 10 and the second annular air collecting chamber 11 through the first air collecting chamber vent hole 22 and the second air collecting chamber vent hole 23 respectively, it reaches the turbine and the cockpit air using parts through the turbine air duct 26 and the cockpit air duct 27. The two groups of positioning pin lugs 7 (each group has six positioning pin ears 7) cooperate with the positioning pins 28 to fix the circumferential position of the total six-stage rectifier 29. Each stage of the rectifier is fixed by two positioning pins 28 in the circumferential 180° direction. The eight pins 9 on the inner surface of the rear end of the casing housing 2 cooperate with the "U"-shaped grooves 31 on the deflector window 30 to fix the circumferential position of the deflector window 30. The three observation window lugs 8 cooperate with the observation window plug 32, are locked during the operation of the engine, and are removed during maintenance, having good maintainability and detectability.

[0045] The actual application effects are as follows

[0046] In terms of strength, the annular casing 1 has passed the assessment of the bearing capacity test under the conditions of the highest working temperature and twice the maximum working pressure. After the test, the annular casing 1 is inspected by the kerosene-chalk method, and the results show no cracks and no damage. In terms of air extraction, within the full operating range, the cooling air extraction requirements of the turbine blades and the safe air use requirements of the pilot are met. In terms of assembly, the assembly method is simple, easy to operate, and saves manpower. In terms of maintainability, the accessibility, operability, and detectability are high. The design and application problems of the composite function compressor casing that integrates the requirements of load-bearing, air extraction, installation, and maintenance are solved.

[0047] The above are only the preferred embodiments of the present invention, and do not limit the patent scope of the present invention. Any equivalent structural transformation made under the inventive concept of the present invention by using the content of the specification and drawings of the present invention, or any direct / indirect application in other related technical fields, is included in the patent protection scope of the present invention.

Claims

1. A composite function compressor casing with a gas collecting cavity structure, Characterized in that, It includes a casing shell (2) and an annular casing (1) composed of a first cavity outer shell (3) and a second cavity outer shell (4); Two annular cavities are arranged on the circumferential surface of the casing shell (2); The first cavity outer shell (3) covers one of the annular cavities to form a first annular gas collecting cavity (10); the second cavity outer shell (4) covers the other annular cavity to form a second annular gas collecting cavity (11); A first cavity air extraction hole (24) is arranged on the first cavity outer shell (3); a second cavity air extraction hole (25) is arranged on the second cavity outer shell (4); the number of the first cavity air extraction holes (24) arranged on the first cavity outer shell (3) is three; the number of the second cavity air extraction holes (25) arranged on the second cavity outer shell (4) is two; Two groups of positioning pin lugs (7) are arranged on the annular casing (1), and the two groups of positioning pin lugs (7) are longitudinally arranged 180° apart, and each group is provided with a plurality of positioning pin lugs (7); positioning pin through holes (201) are arranged on the inner side wall of the casing shell (2) at positions opposite to each positioning pin lug (7); the two groups of positioning pin lugs (7) cooperate with the positioning pins (28) to fix the circumferential position of a total of six-stage rectifiers (29), and each stage of the rectifier is fixed by two positioning pins (28) in the circumferential 180° direction; A plurality of observation window lugs (8) are arranged on the annular casing (1); A first gas collecting cavity ventilation hole (22) is arranged on the inner side wall of the casing shell (2) and communicated with the first annular gas collecting cavity (10), and a second gas collecting cavity ventilation hole (23) is arranged and communicated with the second annular gas collecting cavity (11); A first cavity air extraction mounting seat (5) is welded at the first cavity air extraction hole (24); a second cavity air extraction mounting seat (6) is welded at the second cavity air extraction hole (25); the three first cavity air extraction mounting seats (5) are connected to the turbine air extraction pipe (26), and the two second cavity air extraction mounting seats (6) are connected to the cockpit air extraction pipe (27). After the air flow enters the first annular gas collecting cavity (10) and the second annular gas collecting cavity (11) respectively through the first gas collecting cavity ventilation hole (22) and the second gas collecting cavity ventilation hole (23), it reaches the turbine and the cockpit air-using parts through the turbine air extraction pipe (26) and the cockpit air extraction pipe (27); Eight pins (9) are evenly distributed in a ring on the inner surface of the rear end of the casing shell (2), and the pins (9) are fixed on the inner surface of the rear end of the casing shell (2) by flaring; the pins (9) are used to cooperate with the "U"-shaped grooves on the engine fairing window to fix the circumferential position of the fairing window.

2. A composite function compressor casing with a gas collecting cavity structure according to claim 1, Characterized in that, A lock bottom structure (21) is arranged on the casing shell (2), and the first cavity outer shell (3) and the second cavity outer shell (4) are respectively lapped on the lock bottom structure (21) and welded to the casing shell (2).

3. A composite function compressor casing with a gas collecting cavity structure according to claim 1, Characterized in that, The positioning pin lug (7) and the observation window lug (8) are both fixed on the annular casing (1) by welding. After welding, the positioning pin lug (7) and the observation window lug (8) are drilled by a combined machining method, and all the drilled holes are through holes.

4. A composite function compressor casing with a gas collecting cavity structure according to claim 1, characterized in that a front mounting edge is provided at the front end of the casing housing (2), and a rear mounting edge is provided at the rear end; a front mounting hole (12) is provided on the front mounting edge, and a rear mounting hole (13) is provided on the rear mounting edge.

5. A composite function compressor casing with a gas collecting cavity structure according to claim 1, characterized in that in each group of positioning pin lugs (7), the number of positioning pin lugs (7) is six.

6. A composite function compressor casing with a gas collecting cavity structure according to claim 1, characterized in that the number of the observation window lugs (8) is three, and the three observation window lugs (8) are arranged longitudinally.

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