Deflation structure and aero-engine

Abstract

The invention relates to the technical field of aero-engines, and discloses a deflation structure and an aero-engine, the deflation structure is characterized in that a partition plate is installed in an air cavity of a sprue spreader, and the partition plate divides the air cavity into a first air cavity and a second air cavity; the first air cavity communicates with the fan inner duct flow channel through a first air hole, and the second air cavity communicates with the fan outer duct flow channel through a second air hole. A deflation groove communicated with the first air cavity and the second air cavity is formed in the partition plate; the linkage ring has a non-deflation state for closing the deflation groove and a deflation state for opening the deflation groove; the actuating cylinder drives the linkage ring to be switched between a non-deflation state and a deflation state through the transmission assembly. And the actuating cylinder is arranged outside the aero-engine. The actuator cylinder is installed outside the aero-engine, the installation space of the deflation structure is small, the space is saved, and the performance of the aero-engine is improved; and the linkage ring is matched with the deflation groove for deflation, the structure is simple, the number of parts is small, and the design cost and design difficulty are reduced.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to an air release structure and an aeroengine. Background Art

[0002] like Figure 1 As shown, the existing venting structure located at the diverter cone of the intermediate casing is a sliding door type adjustable venting valve structure that drives the venting sliding door 1 through the existing linkage ring 3; specifically: the actuator 4 drives the existing linkage ring 3 to move through the crank structure 2, and the existing linkage ring 3 drives to open multiple venting sliding doors 1 that are evenly distributed circumferentially on the casing wall hinged at the diverter cone position to achieve internal venting of the fan. The actuator 4 and the crank structure 2 are installed between the high-pressure compressor casing behind the diverter cone and the outer culvert inner flow channel casing, that is, the actuator 4 and the crank structure 2 are located in the aircraft engine. For aircraft engines with limited installation space, the above-mentioned arrangement of the actuator 4 and the crank structure 2 requires too much installation space, seriously occupies the limited space in the engine, and seriously affects the improvement of the overall performance of the engine. Summary of the invention

[0003] In view of this, the present invention provides an air bleed structure to solve the problem that the existing arrangement of the actuator and crank of the air bleed structure located at the intermediate casing diverter cone in the aircraft engine requires too much installation space, seriously occupies the limited space in the engine and seriously affects the overall performance improvement of the engine.

[0004] In a first aspect, the present invention provides a deflation structure, comprising:

[0005] A partition is installed in an air cavity provided in a splitter cone of an aircraft engine, the partition divides the air cavity into a first air cavity and a second air cavity; the first air cavity is connected to an inner flow passage of a fan through a first air hole, and the second air cavity is connected to an outer flow passage of a fan through a second air hole; an air discharge groove connecting the first air cavity and the second air cavity is provided on the partition;

[0006] The linkage ring has a non-deflation state with the deflation groove closed and a deflation state with the deflation groove opened;

[0007] The actuator drives the linkage ring to switch between the non-deflation state and the deflation state through the transmission assembly; and the actuator is arranged outside the aircraft engine. Beneficial effects: The present application adopts the above technical solution to install the actuator outside the aircraft engine, and the deflation structure requires a smaller installation space, saving the limited space in the aircraft engine and improving the overall performance of the aircraft engine; and the linkage ring is used in conjunction with the deflation groove for deflation, which has a simpler structure than the prior art, with fewer parts, reducing the design cost and difficulty; the deflation structure does not require too much space and can be applied to aircraft engines with smaller flow rates.

[0008] Optionally, the transmission assembly includes:

[0009] A driving shaft connected to the actuator;

[0010] An active rod, one end of which is connected to the active shaft;

[0011] A first pin has one end connected to the other end of the active rod; the other end of the first pin is movably connected to the linkage ring, and the actuator is suitable for driving the active shaft to rotate, thereby driving the active rod to rotate around the axis of the active shaft.

[0012] Optionally, the other end of the first pin is movably connected to the linkage ring via a joint bearing.

[0013] Optionally, the axial direction of the driving shaft is perpendicular to the axial direction of the aircraft engine.

[0014] Optionally, it also includes:

[0015] A plurality of rocker arms, the first end of which is rotatably connected to the partition, and the second end of which is rotatably connected to the linkage ring; the rocker arm is suitable for cooperating with the linkage ring to complete the action of closing the venting groove or opening the venting groove. Beneficial effect: The present application adopts the above technical solution, and by setting a plurality of rocker arms, the angular displacement and axial displacement of the linkage ring are coordinated.

[0016] Optionally, the first end of the rocker arm is rotatably connected to the partition through a second pin.

[0017] Optionally, the partition seal is installed in an air cavity provided in a splitter cone of an aircraft engine.

[0018] In a second aspect, the present invention further provides an aircraft engine, comprising the above-mentioned air bleed structure.

[0019] Optionally, the aircraft engine is a turbofan engine. Beneficial effects: The present application adopts the above technical solution. Since the turbofan engine has a small flow rate and a very limited internal space, the air release structure of the present application is very suitable for the turbofan engine.

[0020] Optionally, the aircraft engine is a twin-duct engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a three-dimensional structural schematic diagram of the air release structure in the prior art;

[0023] Figure 2 A schematic cross-sectional view of a degassing structure provided in an embodiment of the present invention;

[0024] Figure 3 It is a schematic diagram of a partial three-dimensional structure of a degassing structure provided in an embodiment of the present invention.

[0025] Description of reference numerals:

[0026] 1. Deflation sliding door; 2. Crank structure; 3. Existing linkage ring; 4. Actuating cylinder; 5. Partition plate; 6. Intermediate casing; 7. First air hole; 8. Second air hole; 9. Deflation groove; 10. Linkage ring; 11. Active shaft; 12. Active rod; 13. First pin; 14. Spherical bearing; 15. Rocker arm; 16. Second pin; 17. First air cavity; 18. Second air cavity. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0028] like Figure 1 As shown, for the sliding door type adjustable deflation valve structure that drives the deflation sliding door 1 through the existing linkage ring 3, the number of parts that need to be designed is relatively large, which significantly increases the design difficulty. Also due to the above reasons, the present application proposes an improved deflation structure.

[0029] like Figures 2 to 3 A specific implementation of the deflation structure shown includes: a partition 5, a linkage ring 10 and an actuator.

[0030] like Figure 2As shown, the partition 5 is installed in the air cavity provided in the splitter cone of the aircraft engine. Specifically, the partition 5 is sealed and installed in the air cavity provided in the splitter cone of the aircraft engine, and the splitter cone is located in the intermediate casing 6. The partition 5 divides the air cavity into a first air cavity 17 and a second air cavity 18; the first air cavity 17 is connected to the inner flow channel of the fan through the first air hole 7, and the first air cavity 17 is also called the inner air cavity. When the air cavity is annular, the partition 5 is also annular. The second air cavity 18 is connected to the outer flow channel of the fan through the second air hole 8, and the second air cavity 18 is also called the outer air cavity; a venting groove 9 connecting the first air cavity 17 and the second air cavity 18 is provided on the partition 5. The linkage ring 10 has a non-venting state with the venting groove 9 closed; and a venting state with the venting groove 9 opened. The actuator drives the linkage ring 10 to switch between the non-venting state and the venting state through the transmission assembly; and the actuator is arranged on the outside of the aircraft engine. Among them, Figure 2 The arrows in the figure indicate the flow direction of the gas in the deflated state.

[0031] Specifically, Figure 2 and Figure 3 As shown, the transmission assembly includes: a driving shaft 11, an active rod 12 and a first pin 13. The driving shaft 11 is connected to the actuator cylinder; one end of the active rod 12 is connected to the driving shaft 11. One end of the first pin 13 is connected to the other end of the active rod 12; the other end of the first pin 13 is movably connected to the linkage ring 10, and more specifically, the other end of the first pin 13 is movably connected to the linkage ring 10 through a joint bearing 14. The actuator cylinder is suitable for driving the driving shaft 11 to rotate, and then driving the active rod 12 to rotate around the axis of the driving shaft 11. The axial direction of the driving shaft 11 is perpendicular to the axial direction of the aircraft engine.

[0032] Further, such as Figure 3 As shown, the deflation structure of the present application further includes: a plurality of rocker arms 15, the first end of the rocker arms 15 is rotatably connected to the partition 5, specifically, the first end of the rocker arm 15 is rotatably connected to the partition 5 through a second pin 16; the second end of the rocker arm 15 is rotatably connected to the linkage ring 10; a plurality of rocker arms 15 are arranged at intervals in the circumference of the linkage ring 10. The rocker arm 15 is suitable for cooperating with the linkage ring 10 to complete the action of closing the deflation groove 9 or opening the deflation groove 9. The first end and the second end of the rocker arm 15 are arranged opposite to each other.

[0033] The working principle of the deflation structure described in the present application is briefly described as follows: when the aircraft engine needs to be deflated, the active shaft 11 is driven by the actuator, thereby driving the active rod 12 to rotate around the axis of the active shaft 11, and the active rod 12 is connected to the linkage ring 10 through the first pin 13 and the joint bearing 14. Therefore, when the active rod 12 rotates, the linkage ring 10 will also rotate around the axis of the aircraft engine and produce axial displacement, thereby opening the deflation groove 9 for deflation.

[0034] The present application also provides an aircraft engine, including the above-mentioned bleed structure. Specifically, the aircraft engine is a turbofan engine; the aircraft engine is a dual-duct engine, and the above-mentioned bleed structure is provided in each duct of the aircraft engine, and the two bleed structures are controlled simultaneously to bleed air simultaneously. The applicant has completed the three-dimensional modeling and strength evaluation of the dual-duct bleed structure, and it has been verified in practice that the bleed structure described in the present application can be maturely applied in many aircraft engines, proving that the bleed structure described in the present application is feasible and achieves the expected effect.

[0035] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A deflation structure, characterized in that: include: A partition (5) is installed in an air cavity provided in a splitter cone of an aircraft engine, the partition (5) dividing the air cavity into a first air cavity (17) and a second air cavity (18); the first air cavity (17) is connected to an inner flow passage of a fan through a first air hole (7), and the second air cavity (18) is connected to an outer flow passage of the fan through a second air hole (8); an air discharge groove (9) connecting the first air cavity (17) and the second air cavity (18) is provided on the partition (5); The linkage ring (10) has a non-deflation state in which the deflation groove (9) is closed, and a deflation state in which the deflation groove (9) is opened; The actuator drives the linkage ring (10) to switch between the non-deflated state and the deflated state through a transmission component; and the actuator is arranged outside the aircraft engine.

2. The degassing structure according to claim 1, characterized in that: The transmission assembly comprises: A driving shaft (11) connected to the actuator; An active rod (12), one end of which is connected to the active shaft (11); A first pin (13) has one end connected to the other end of the active rod (12); the other end of the first pin (13) is movably connected to the linkage ring (10), and the actuator is suitable for driving the active shaft (11) to rotate, thereby driving the active rod (12) to rotate around the axis of the active shaft (11).

3. The degassing structure according to claim 2, characterized in that: The other end of the first pin (13) is movably connected to the linkage ring (10) via a joint bearing (14).

4. The air release structure according to claim 2 or 3, characterized in that: The axial direction of the driving shaft (11) is perpendicular to the axial direction of the aircraft engine.

5. The degassing structure according to any one of claims 1 to 3, characterized in that: Also includes: A plurality of rocker arms (15) are provided, wherein the first end of the rocker arms (15) is rotatably connected to the partition plate (5), and the second end of the rocker arms (15) is rotatably connected to the linkage ring (10); the rocker arms (15) are suitable for cooperating with the linkage ring (10) to complete the action of closing the air release groove (9) or opening the air release groove (9).

6. The degassing structure according to claim 5, characterized in that: The first end of the rocker arm (15) is rotatably connected to the partition plate (5) via a second pin (16).

7. The degassing structure according to any one of claims 1 to 3, characterized in that: The partition plate (5) is sealed and installed in an air cavity provided in the splitter cone of the aircraft engine.

8. An aircraft engine, characterized in that: The invention comprises the degassing structure according to any one of claims 1 to 7.

9. The aircraft engine according to claim 8, characterized in that: The aircraft engine is a turbofan engine.

10. The aircraft engine according to claim 8, characterized in that: The aircraft engine is a dual-duct engine.

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