A deflation structure and an aeroengine

Abstract

The application relates to the technical field of aero-engines, and discloses a bleeder structure and an aero-engine. The bleeder structure comprises: a partition plate installed in a gas cavity of a splitter cone, the partition plate divides the gas cavity into a first gas cavity and a second gas cavity; the first gas cavity is communicated with an inner bypass flow channel of a fan through a first gas hole, and the second gas cavity is communicated with an outer bypass flow channel of the fan through a second gas hole; a bleeder groove for communicating the first gas cavity and the second gas cavity is arranged on the partition plate; a linkage ring has a non-bleeding state of closing the bleeder groove and a bleeding state of opening the bleeder groove; an actuating cylinder drives the linkage ring to switch between the non-bleeding state and the bleeding state through a transmission assembly; and the actuating cylinder is arranged outside the aero-engine. The application has the advantages that the actuating cylinder is arranged outside the aero-engine, the installation space of the bleeder structure is small, space is saved, and the performance of the aero-engine is improved; and the linkage ring is used in cooperation with the bleeder groove to bleed, the structure is simple, the number of parts is small, and the design cost and difficulty are reduced.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a venting structure and an aero-engine. Background Technology

[0002] like Figure 1 As shown, the existing venting structure located at the intermediate casing splitter cone is a pull-door adjustable venting valve structure that drives the venting valve 1 through the existing linkage ring 3. Specifically, the actuator 4 drives the existing linkage ring 3 to actuate via the crank structure 2, and the existing linkage ring 3 drives the opening of multiple venting valves 1 that are evenly distributed circumferentially on the casing wall at the splitter cone position, thereby realizing venting within the fan. The actuator 4 and crank structure 2 are installed between the high-pressure compressor casing and the outer bypass inner flow channel casing after the splitter cone, that is, the actuator 4 and crank structure 2 are located inside the aero-engine. For aero-engines with limited installation space, the above-mentioned arrangement of the actuator 4 and crank structure 2 requires too much installation space, seriously occupying the limited space inside the engine and severely affecting the improvement of the overall engine performance. Summary of the Invention

[0003] In view of this, the present invention provides a venting structure to solve the problem that the existing venting structure located at the intermediate casing splitter cone has an actuator and crank located inside the aero engine, which requires too much installation space, seriously occupies the limited space inside the engine, and seriously affects the improvement of the overall engine performance.

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

[0005] A baffle plate is installed inside the air chamber of the splitter cone of the aero engine, and the baffle plate divides the air chamber into a first air chamber and a second air chamber; the first air chamber is connected to the inner flow channel of the fan through a first air hole, and the second air chamber is connected to the outer flow channel of the fan through a second air hole; an air venting groove is provided on the baffle plate to connect the first air chamber and the second air chamber.

[0006] The linkage ring has a non-venting state with the vent groove closed, and a venting state with the vent groove open.

[0007] An actuator, via a transmission assembly, drives the linkage ring to switch between the non-venting state and the venting state; and the actuator is located externally to the aero-engine. Beneficial effects: This application adopts the above technical solution, installing the actuator externally to the aero-engine, requiring less installation space for the venting structure, saving limited space within the aero-engine and improving the overall performance of the aero-engine; furthermore, using a linkage ring in conjunction with a venting groove for venting results in a simpler structure than existing technologies, fewer parts, and reduced design costs and complexity; the venting structure does not require a large space and is suitable for aero-engines with smaller flow rates.

[0008] Optionally, the transmission assembly includes:

[0009] The drive shaft is connected to the actuator cylinder;

[0010] The drive rod is connected at one end to the drive shaft;

[0011] The first pin has one end connected to the other end of the drive rod; the other end of the first pin is movably connected to the linkage ring, and the actuating cylinder is adapted to drive the drive shaft to rotate, thereby driving the drive rod to rotate around the axis of the drive shaft.

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

[0013] Optionally, the axial direction of the drive shaft is perpendicular to the axial direction of the aero-engine.

[0014] Optionally, it also includes:

[0015] Multiple rocker arms are provided, with their first ends rotatably connected to the partition plate and their second ends rotatably connected to the linkage ring. The rocker arms are adapted to cooperate with the linkage ring to close or open the venting groove. Beneficial effect: This application adopts the above technical solution, and by setting multiple rocker arms, ensures coordinated angular and axial displacement of the linkage ring.

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

[0017] Optionally, the diaphragm is sealed and installed within the air chamber of the splitter cone of the aero-engine.

[0018] Secondly, the present invention also provides an aircraft engine including the aforementioned venting structure.

[0019] Optionally, the aero-engine is a turbofan engine. Beneficial effects: This application adopts the above technical solution. Because turbofan engines have relatively small airflow and limited internal space, the venting structure described in this application is very suitable for turbofan engines.

[0020] Optionally, the aircraft engine is a twin-ducted engine. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 A three-dimensional structural diagram of the venting structure in the prior art;

[0023] Figure 2 This is a cross-sectional view of the venting structure provided in an embodiment of the present invention;

[0024] Figure 3 This is a partial three-dimensional structural diagram of the venting structure provided in an embodiment of the present invention.

[0025] Explanation of reference numerals in the attached figures:

[0026] 1. Air release valve; 2. Crank structure; 3. Existing linkage ring; 4. Actuating cylinder; 5. Baffle plate; 6. Intermediate housing; 7. First air vent; 8. Second air vent; 9. Air release groove; 10. Linkage ring; 11. Drive shaft; 12. Drive rod; 13. First pin; 14. Spherical bearing; 15. Rocker arm; 16. Second pin; 17. First air chamber; 18. Second air chamber. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] like Figure 1 As shown, the existing adjustable venting valve structure that uses the linkage ring 3 to drive the venting valve 1 requires a large number of parts, significantly increasing the design difficulty. For these reasons, this application proposes an improved venting structure.

[0029] like Figures 2 to 3 One specific embodiment of the venting structure shown includes: a partition 5, a linkage ring 10, and an actuating cylinder.

[0030] like Figure 2As shown, the baffle 5 is installed within the air chamber of the air divider cone of the aero-engine. Specifically, the baffle 5 is sealed within the air chamber of the air divider cone, which is located within the intermediate casing 6. The baffle 5 divides the air chamber into a first air chamber 17 and a second air chamber 18. The first air chamber 17 is connected to the fan inner flow channel through a first air hole 7, and is also referred to as the inner air chamber. When the air chamber is annular, the baffle 5 is also annular. The second air chamber 18 is connected to the fan outer flow channel through a second air hole 8, and is also referred to as the outer flow chamber. A venting groove 9 is provided on the baffle 5, connecting the first air chamber 17 and the second air chamber 18. The linkage ring 10 has a non-venting state with the venting groove 9 closed, and a venting state with the venting groove 9 open. The actuator cylinder drives the linkage ring 10 to switch between the non-venting state and the venting state through a transmission assembly; and the actuator cylinder is located outside the aero-engine. Figure 2 The arrows in the diagram indicate the direction of gas flow during the venting process.

[0031] Specifically, such as Figure 2 and Figure 3 As shown, the transmission assembly includes: a drive shaft 11, a drive rod 12, and a first pin 13. The drive shaft 11 is connected to the actuating cylinder; one end of the drive rod 12 is connected to the drive shaft 11. One end of the first pin 13 is connected to the other end of the drive rod 12; the other end of the first pin 13 is movably connected to the linkage ring 10, more specifically, the other end of the first pin 13 is movably connected to the linkage ring 10 via a spherical bearing 14. The actuating cylinder is adapted to drive the drive shaft 11 to rotate, thereby driving the drive rod 12 to rotate around the axis of the drive shaft 11. The axial direction of the drive shaft 11 is perpendicular to the axial direction of the aero-engine.

[0032] Furthermore, such as Figure 3 As shown, the venting structure of this application further includes: a plurality of rocker arms 15, the first end of which is rotatably connected to the partition plate 5. Specifically, the first end of the rocker arm 15 is rotatably connected to the partition plate 5 via a second pin 16; the second end of the rocker arm 15 is rotatably connected to the linkage ring 10; the plurality of rocker arms 15 are spaced apart around the circumference of the linkage ring 10. The rocker arms 15 are adapted to cooperate with the linkage ring 10 to complete the action of closing or opening the venting 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 venting structure described in this application is briefly described as follows: When the aero-engine needs to vent, the actuator drives the drive shaft 11, which in turn drives the drive rod 12 to rotate around the axis of the drive shaft 11. The drive rod 12 is connected to the linkage ring 10 through the first pin 13 and the spherical bearing 14. Therefore, when the drive rod 12 rotates, the linkage ring 10 also rotates around the axis of the aero-engine and generates axial displacement, thereby opening the venting slot 9 to vent.

[0034] This application also provides an aero-engine, including the aforementioned bleed structure. Specifically, the aero-engine is a turbofan engine; the aero-engine is a twin-ducted engine, and the bleed structure is provided in each duct of the aero-engine. Simultaneous control of the two bleed structures allows for simultaneous bleed operation. The applicant has completed the 3D modeling and strength evaluation of the twin-ducted bleed structure, and practical verification shows that the bleed structure described in this application can be maturely applied in many aero-engines, proving the feasibility of the bleed structure and achieving the expected results.

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

Claims

1. A deflation structure, characterized by, include: A baffle (5) is installed in the air chamber of the splitter cone of the aero engine. The baffle (5) divides the air chamber into a first air chamber (17) and a second air chamber (18). The first air chamber (17) is connected to the inner flow channel of the fan through a first air hole (7), and the second air chamber (18) is connected to the outer flow channel of the fan through a second air hole (8). An air venting groove (9) is provided on the baffle (5) to connect the first air chamber (17) and the second air chamber (18). The linkage ring (10) has a non-venting state with the vent groove (9) closed; and a venting state with the vent groove (9) opened. The actuator drives the linkage ring (10) to switch between the non-venting state and the venting state through the transmission component; Furthermore, the actuator is located outside the aircraft engine; The transmission assembly includes: The drive shaft (11) is connected to the actuating cylinder; One end of the active rod (12) is connected to the active shaft (11); The first pin (13) is connected at one end 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); the actuating cylinder is adapted to drive the active shaft (11) to rotate, thereby driving the active rod (12) to rotate around the axis of the active shaft (11); Also includes: Multiple rocker arms (15) are rotatably connected at their first end to the partition plate (5) and at their second end to the linkage ring (10). The rocker arms (15) are adapted to cooperate with the linkage ring (10) to complete the action of closing the venting groove (9) or opening the venting groove (9).

2. The vent structure of claim 1, wherein The other end of the first pin (13) is movably connected to the linkage ring (10) via a joint bearing (14).

3. The vent structure of claim 1 or 2, wherein, The axial direction of the drive shaft (11) is perpendicular to the axial direction of the aero-engine.

4. The vent structure of claim 1, wherein The first end of the rocker arm (15) is rotatably connected to the partition plate (5) via a second pin (16).

5. The vent structure of claim 1 or 2, wherein The partition (5) is sealed and installed in the air chamber provided in the flow divider cone of the aero engine.

6. An aeroengine characterised in that, The venting structure includes any one of claims 1-5.

7. The aeroengine of claim 6, wherein, The aircraft engine is a turbofan engine.

8. The aeroengine of claim 6, wherein, The aircraft engine is a twin-ducted engine.

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