A composite strut for a variable cycle engine combustion chamber

Abstract

The application discloses a composite support plate for a variable cycle engine combustion chamber and relates to the field of aero-engine combustion chambers, which comprises a radial support plate arranged at an inlet position of the variable cycle engine combustion chamber; a circumferential support plate comprises a plurality of support plate bodies distributed along the circumference, the support plate body comprises a connecting portion, a support plate leading edge portion and a support plate main body portion, the plurality of support plate main body portions are connected into a cylindrical structure along the circumference and are fixedly connected with the radial support plate; one end of the support plate leading edge portion is connected with the support plate main body portion through the connecting portion, and the support plate leading edge portion can rotate radially; when the support plate leading edge portion rotates outward to the maximum angle, the side walls of the adjacent two support plate leading edge portions are tightly fitted, at this time, the plurality of support plate leading edge portions are connected into a horn mouth structure. When facing different direction air flows, the radial angle of the support plate leading edge portion can be changed, so that the collision and separation of the circumferential support plate and the air flow are reduced, and the total pressure loss can be reduced as much as possible when facing different direction air flows.

Description

Technical Field

[0001] This invention relates to the field of aero-engine combustion chamber technology, and in particular to a composite support plate for a variable cycle engine combustion chamber. Background Technology

[0002] A variable cycle engine (VCE) is a highly advanced aero-engine design that dynamically adjusts its operating mode and thermodynamic cycle parameters according to different flight conditions to achieve broader performance optimization. VCE engines are typically designed with at least two operating modes, such as turbofan mode (suitable for subsonic flight, emphasizing fuel efficiency) and turbojet mode (suitable for supersonic flight, emphasizing thrust output). By changing key parameters such as bypass ratio, turbine inlet temperature, airflow, and pressure ratio, this type of engine can switch between different flight phases (such as takeoff, subsonic cruise, and supersonic flight) to achieve optimal fuel efficiency and thrust output.

[0003] Because variable cycle engines need to switch between two operating modes, the intake conditions of the combustion chamber annulus are complex, resulting in high intake pressure loss, high temperature, and high speed. When a variable cycle engine operates in different states, the airflow will generate large velocity angles in the radial and circumferential directions. This may cause significant airflow separation on the flame stabilizer surface, leading to a decrease in the total pressure recovery coefficient of the combustion device.

[0004] The engine's combustion chamber is equipped with a fixedly arranged composite support plate, a structural component used to support, guide, and stabilize the combustion process. Through specific design and structure, it optimizes airflow and fuel distribution within the combustion chamber, thereby improving combustion efficiency and stability. The composite support plate, with its unique structure and design, guides the flow of the fuel-air mixture within the combustion chamber, ensuring its uniform distribution. The grooves and oxidation pores in the composite support plate create a recirculation zone, enhancing fuel-air mixing and improving combustion efficiency. Simultaneously, the composite support plate can withstand the harsh environment of high temperature, high pressure, and vibration within the combustion chamber, ensuring stable operation.

[0005] However, in existing technologies, composite support plates are all fixed structures. In the combustion chamber of a variable-cycle engine, a situation not encountered in a conventional combustion chamber arises: the radial flow angle of the inlet airflow varies significantly under different operating modes. When the radial angle is too large, the airflow collides and separates from the annular support plate portion of the composite support plate, resulting in a large total pressure loss and ultimately leading to a decrease in aero-engine performance. Therefore, existing composite support plate structures cannot reduce the total pressure loss of variable-cycle engines. Thus, there is an urgent need to design a composite support plate structure that can minimize the total pressure loss when facing airflow from different directions. Summary of the Invention

[0006] The purpose of this invention is to provide a composite support plate for the combustion chamber of a variable cycle engine to solve the problems existing in the prior art. When facing incoming flow from different directions, the radial angle of the leading edge of the support plate can be changed, thereby reducing the collision and separation between the incoming flow and the circumferential support plate, so as to minimize the total pressure loss when facing incoming flow from different directions.

[0007] To achieve the above objectives, the present invention provides the following solution:

[0008] This invention provides a composite support plate for the combustion chamber of a variable cycle engine, comprising:

[0009] Radial support plate, fixedly installed at the inlet position of the combustion chamber of the variable cycle engine;

[0010] A circumferential support plate includes multiple support plate bodies distributed circumferentially. Each support plate body includes a connecting part, a front edge part, and a main body part. The multiple main body parts are joined together circumferentially to form a cylindrical structure and are fixedly connected to the radial support plate.

[0011] One end of the front edge of the support plate is connected to the main body of the support plate through the connecting part, and the front edge of the support plate can rotate radially;

[0012] When the front edge of the support plate rotates outward to its maximum angle, the sidewalls of two adjacent front edges of the support plates fit together tightly, and at this time, multiple circumferentially distributed front edges of the support plates are assembled into a trumpet-shaped structure.

[0013] Optionally, the sidewall of the front edge of the support plate is a sloping structure, the two sidewalls of the front edge of the support plate are inclined in opposite directions, and the two sidewalls of the two adjacent front edges of the support plate can fit together in opposite directions; when the front edge of the support plate rotates inward, the rotation angles of the two adjacent front edges of the support plate are different, so that the sidewalls of the two adjacent front edges of the support plate are radially misaligned and fit together.

[0014] Optionally, the connecting part includes two connecting seats fixedly disposed at one end of the main body of the support plate. Each connecting seat has a connecting through hole, and a connecting shaft passes through the connecting through holes of the two connecting seats. A rotating seat is sleeved on the connecting shaft and is located between the two connecting seats. One end of the front edge of the support plate is fixedly connected to the outer wall of the rotating seat. The rotating seat is connected to a driving device, which can drive the rotating seat to rotate around the connecting shaft, thereby driving the front edge of the support plate to rotate radially synchronously.

[0015] Optionally, the connecting part includes two connecting seats fixedly disposed at one end of the main body of the support plate. Each connecting seat has a connecting through hole. A connecting shaft is movably inserted through the connecting through holes of the two connecting seats. A rotating seat is fixedly sleeved on the connecting shaft. The rotating seat is located between the two connecting seats. One end of the front edge of the support plate is fixedly connected to the outer wall of the rotating seat. The connecting shaft is driven by a driving device. The driving device can drive the connecting shaft to rotate within the connecting through hole, thereby driving the rotating seat and the front edge of the support plate to rotate synchronously radially.

[0016] Optionally, one end of the rotating seat is fixedly connected to the front edge of the support plate, and the other end is fixedly connected to an actuating crank. An actuator is connected to the end of the actuating crank, and the actuator can pull the actuating crank to drive the rotating seat to rotate around the connecting shaft.

[0017] Optionally, the main body of the support plate includes an inner plate and an outer plate arranged in parallel, and the actuator and the actuating crank are both located between the inner plate and the outer plate.

[0018] Optionally, the outer plates of the multiple main body parts are circumferentially fixedly assembled to form an outer cylindrical structure, and the inner plates of the multiple main body parts are circumferentially fixedly assembled to form an inner cylindrical structure; the radial support plate is radially fixedly inserted through the outer cylindrical structure and the inner cylindrical structure.

[0019] Optionally, a cooling air chamber is provided in the front edge of the support plate, and a cooling air supply device is connected to one end of the cooling air chamber through a cooling air flow channel.

[0020] Optionally, the upper and lower ends of the front edge of the support plate are provided with a plurality of cooling through holes, which are connected to the cooling air chamber and are arranged at an angle.

[0021] Optionally, the maximum outward rotation angle of the front edge of the support plate is 12°. o .

[0022] The present invention achieves the following technical effects compared to the prior art:

[0023] The leading edge of the support plate in this invention can rotate radially, thereby changing the leading edge angle of the circumferential support plate. When the airflow direction in front of the combustion chamber changes, the leading edge angle of the circumferential support plate can be adjusted to avoid excessive airflow angle leading to airflow separation and loss. The radial flow angle of the inlet airflow varies significantly under different operating conditions. When the radial angle of the inlet airflow is too large, the inlet airflow will collide and separate with the circumferential support plate in the composite support plate, resulting in a large total pressure loss and ultimately leading to a decrease in aero-engine performance. This invention reduces flow separation caused by the angle of attack when the inlet flow direction becomes larger due to changes in combustion chamber operating conditions. This reduces pressure loss and improves combustion organization under these conditions. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the airflow modes of a dual-variable turbofan engine.

[0026] Figure 2 This is a schematic diagram of the airflow in the turbojet mode of a dual-variable engine.

[0027] Figure 3 This is a schematic diagram of a partial structure of the composite support plate;

[0028] Figure 4 This is a schematic diagram of the support plate body structure of the present invention;

[0029] Figure 5 This is a schematic diagram of the cooling air chamber structure inside the front edge of the support plate of the present invention;

[0030] Figure 6 This is a schematic diagram of the front edge of the support plate after rotation.

[0031] Figure 7 This is a schematic diagram showing the sidewalls of the front edges of two adjacent support plates fitting together when the front edge of the support plate of the present invention is rotated outward to the maximum angle.

[0032] Figure 8 This is a schematic diagram showing the misalignment and fit of the side walls of the front edges of two adjacent support plates when the front edge of the support plate of the present invention is rotated inward at a certain angle.

[0033] In the figure: 100-composite support plate, 1-circumferential support plate, 101-front edge of support plate, 102-connecting part, 1021-connecting seat, 1022-rotating seat, 1023-actuating crank, 103-main body of support plate, 1031-outer plate, 1032-inner plate, 104-cooling air chamber, 105-cooling through hole, 2-radial support plate, 200-combustion chamber. Detailed Implementation

[0034] 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, and 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.

[0035] The purpose of this invention is to provide a composite support plate for the combustion chamber of a variable cycle engine to solve the problems existing in the prior art. When facing incoming flow from different directions, the radial angle of the leading edge of the support plate can be changed, thereby reducing the collision and separation between the incoming flow and the circumferential support plate, so as to minimize the total pressure loss when facing incoming flow from different directions.

[0036] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] like Figure 1 and Figure 2 As shown, Figure 1 and Figure 2 The arrows in the diagram indicate the airflow direction. When the dual-variable engine is in turbofan mode, the inlet airflow direction of its combustion chamber 200 is similar to that of a conventional engine. Therefore, its airflow does not generate large velocity angles in the radial and circumferential directions. However, when its operating condition changes to turbojet mode, the inlet airflow angle of the combustion chamber 200 changes, generating large velocity angles in the radial and circumferential directions. When the radial angle of the inlet airflow of the combustion chamber 200 is too large, the airflow will collide and separate with the circumferential support plate in the composite support plate 100, resulting in a large total pressure loss and ultimately leading to a decrease in the performance of the aero-engine.

[0038] To address the aforementioned problems, the present invention provides a composite support plate 100 for a variable cycle engine combustion chamber 200, such as... Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8As shown, a radial support plate 2 is fixedly installed at the inlet position of the combustion chamber 200 of the variable cycle engine, which serves to support and fix it. The radial support plate 2 is connected to a circumferential support plate 1 arranged in a ring. The circumferential support plate 1 in this invention includes multiple support plate bodies distributed along the circumference. Each support plate body includes a support plate main body 103. The multiple support plate main bodies 103 are spliced ​​together along the circumference to form a cylindrical structure. The multiple support plate main bodies 103 can be spliced ​​together to form a cylindrical structure as a whole, or other fixed and sealed connection methods can be used to form a cylindrical structure as a whole and fix it to the radial support plate 2. This part realizes the functions of fuel injection, flame stabilization and structural support.

[0039] The main body of the support plate 103 is provided with a connecting part 102 at one end away from the combustion chamber 200. One end of the front edge of the support plate 101 is connected to the main body of the support plate 103 through the connecting part 102, and the front edge of the support plate 101 can rotate radially to change the angle in conjunction with the connecting part 102, while effectively guiding the airflow. The connecting part 102 of the present invention is similar to a hinge structure, which can realize the movable connection between the main body of the support plate 103 and the front edge of the support plate 101. Through the actuation device provided in the main body of the main plate, the front edge of the support plate 101 can be driven to rotate around the hinge structure. The actuation device is an existing structure and is not shown in the figure.

[0040] In order to ensure that the multiple front edges 101 of the support plates of the present invention can always be assembled into a whole annular air intake channel structure when they rotate radially to different angles, the side walls of the front edges 101 of the support plates are designed as inclined structures. The two side walls of the front edges 101 of the support plates are inclined in opposite directions, so that the radial cross section of the front edges 101 of the support plates is a trapezoidal structure. The two side walls of two adjacent front edges 101 of the support plates are inclined in opposite directions, that is, the trapezoidal directions formed by the cross sections of two adjacent front edges 101 of the support plates are opposite. Thus, when the front edges 101 of the support plates rotate outward to the maximum angle, the side walls of two adjacent front edges 101 of the support plates are tightly fitted, and at this time, the multiple circumferentially distributed front edges 101 of the support plates are assembled into a trumpet-shaped structure.

[0041] For the circumferential support plate 1, changing the radial angle also changes the diameter of the annulus, affecting the continuity of the circumferential support plate 1. Furthermore, due to the thickness of the circumferential support plate 1, a design similar to a vector nozzle is not suitable. To ensure the guiding capacity of the circumferential support plate 1, the leading edge 101 of the circumferential support plate 1 is designed to fit together perfectly when rotated outward to its maximum angle, i.e., when rotated to its maximum diameter. When the angle of the leading edge 101 decreases, the rotation angle of adjacent leading edges 101 is controlled to slightly offset them radially. This allows for a tight fit between the leading edges 101 at different rotation angles. Specifically, when the leading edge 101 rotates inward, the rotation angles of adjacent leading edges 101 are different, causing the sidewalls of adjacent leading edges 101 to be radially misaligned and fitted together. This allows for a unidirectional rotation angle of 12 degrees, and larger rotation angles can be achieved by adjusting the dimensional parameters.

[0042] In one specific embodiment, the connecting part 102 adopts two cylindrical connecting seats 1021 fixedly disposed at one end of the main body 103 of the support plate. The connecting seats 1021 have coaxial connecting through holes. A connecting shaft passes through the connecting through holes of the two connecting seats 1021, and a rotating seat 1022 is sleeved on the connecting shaft. The rotating seat 1022 is located between the two connecting seats 1021, so that the connecting seats 1021 can limit the rotating seat 1022 at both ends, allowing it to only rotate around the connecting shaft and not move axially along the connecting shaft. The front edge 101 of the support plate... One end is integrally formed or fixedly connected to the outer wall of the rotating seat 1022; the other end of the rotating seat 1022 is fixedly connected to an inclined actuating crank 1023, and the end of the actuating crank 1023 is connected to an actuator. The actuator can pull the actuating crank 1023 through the connecting rod structure, so that it drives the rotating seat 1022 to rotate around the connecting shaft, thereby driving the front edge of the support plate 101 to rotate radially synchronously. The actuator and connecting rod structure are existing technologies, so they will not be described in detail. The connecting rod can be driven by a motor or piston to drive the actuating crank 1023 to change the angle of the front edge of the support plate 101.

[0043] In another embodiment, in addition to the above-mentioned method of directly controlling the rotating seat 1022 to realize the radial rotation of the front edge 101 of the support plate, the connecting shaft can also be movably inserted into the connecting through hole of the two connecting seats 1021. The rotating seat 1022 is fixedly sleeved on the connecting shaft. One end of the connecting shaft is connected to the drive device. The drive device controls the connecting shaft to rotate in the connecting through hole, thereby driving the rotating seat 1022 and the front edge 101 of the support plate to rotate radially synchronously.

[0044] The main body 103 of this embodiment includes an inner plate 1032 and an outer plate 1031 arranged in parallel. The design of the main body 103 is roughly the same as that of a conventional composite support plate 100, with the outer plate 1031, inner plate 1032, and fuel injector rod achieving flame stabilization and fuel supply functions. A motor or hydraulic device is installed in the empty space within the outer plate 1031 and inner plate 1032 as an actuator to push and pull the crank 1023, thereby realizing the movement of the front end. The outer plates 1031 of multiple main bodies are circumferentially fixed and assembled to form an outer cylindrical structure, and the inner plates 1032 of multiple main bodies are circumferentially fixed and assembled to form an inner cylindrical structure; the radial support plate 2 is radially fixed through the outer cylindrical structure and the inner cylindrical structure to achieve fixation.

[0045] In this embodiment, when the front edge 101 of the support plate needs to be cooled, it can be designed as a hollow shell structure. A cooling air chamber 104 is provided inside the front edge 101 of the support plate. Multiple cooling through holes 105 are provided at the upper and lower ends of the front edge 101 of the support plate. The cooling through holes 105 are connected to the cooling air chamber 104, and the air outlet of the cooling through holes 105 is arranged inclined towards the side closer to the combustion chamber 200. One end of the cooling air chamber 104 is connected to a cooling air supply device through a cooling airflow channel. Air is supplied into the cooling air chamber 104 and blown out through the cooling through holes 105 to ensure the normal operation of the device under high temperature incoming flow conditions. When cooling is not required, the front edge 101 of the support plate can be a solid part.

[0046] This invention, while possessing the advantages of a simpler structure and lower total pressure loss of the traditional composite support plate 100, adds a movable leading edge 101 to adapt to more variable incoming flow angles. This results in better mixing and combustion performance under the complex incoming flow conditions of a dual-variable engine. The composite support plate 100, as a flame stabilizer for the engine, has a specific structure and operating method that are existing technologies. This invention improves upon this existing structure by allowing the leading edge angle of the circumferential support plate to be radially changed. When the dual-variable engine switches from turbofan mode to turbojet mode, the incoming flow direction in the combustion chamber 200 becomes larger radially. At this time, by controlling the actuation device, the leading edge 101 of the circumferential support plate in the combustion chamber 200 is expanded outward by an angle, reducing flow separation caused by the angle of attack. Ultimately, this reduces pressure loss and improves the combustion organization under this condition.

[0047] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A composite support plate for the combustion chamber of a variable cycle engine, characterized in that, include: Radial support plate, fixedly installed at the inlet position of the combustion chamber of the variable cycle engine; A circumferential support plate includes multiple support plate bodies distributed circumferentially. Each support plate body includes a connecting part, a front edge part, and a main body part. The multiple main body parts are joined together circumferentially to form a cylindrical structure and are fixedly connected to the radial support plate. One end of the front edge of the support plate is connected to the main body of the support plate through the connecting part, and the front edge of the support plate can rotate radially; When the front edge of the support plate rotates outward to the maximum angle, the sidewalls of two adjacent front edges of the support plate fit tightly together, and at this time, multiple circumferentially distributed front edges of the support plate are assembled into a trumpet-shaped structure. The sidewall of the front edge of the support plate has an inclined structure. The two sidewalls of the front edge of the support plate have opposite inclination directions, and the two sidewalls of the two adjacent front edges of the support plate can fit together have opposite inclination directions. When the front edge of the support plate rotates inward, the rotation angles of the two adjacent front edges of the support plate are different, so that the sidewalls of the two adjacent front edges of the support plate are radially misaligned and fit together. A cooling air chamber is provided in the front edge of the support plate. A cooling air supply device is connected to one end of the cooling air chamber through a cooling air flow channel. Multiple cooling through holes are provided at the upper and lower ends of the front edge of the support plate. The cooling through holes are connected to the cooling air chamber and are arranged at an angle.

2. The composite support plate for a variable cycle engine combustion chamber according to claim 1, characterized in that, The connecting part includes two connecting seats fixedly disposed at one end of the main body of the support plate. Each connecting seat has a connecting through hole, and a connecting shaft passes through the connecting through holes of the two connecting seats. A rotating seat is sleeved on the connecting shaft and is located between the two connecting seats. One end of the front edge of the support plate is fixedly connected to the outer wall of the rotating seat. The rotating seat is connected to a driving device, which can drive the rotating seat to rotate around the connecting shaft, thereby driving the front edge of the support plate to rotate radially synchronously.

3. The composite support plate for a variable cycle engine combustion chamber according to claim 1, characterized in that, The connecting part includes two connecting seats fixedly disposed at one end of the main body of the support plate. Each connecting seat has a connecting through hole. A connecting shaft is movably inserted through the connecting through holes of the two connecting seats. A rotating seat is fixedly sleeved on the connecting shaft. The rotating seat is located between the two connecting seats. One end of the front edge of the support plate is fixedly connected to the outer wall of the rotating seat. The connecting shaft is driven by a driving device. The driving device can drive the connecting shaft to rotate in the connecting through hole, thereby driving the rotating seat and the front edge of the support plate to rotate synchronously radially.

4. The composite support plate for a variable cycle engine combustion chamber according to claim 2, characterized in that, One end of the rotating seat is fixedly connected to the front edge of the support plate, and the other end is fixedly connected to an actuating crank. An actuator is connected to the end of the actuating crank, and the actuator can pull the actuating crank to drive the rotating seat to rotate around the connecting shaft.

5. The composite support plate for a variable cycle engine combustion chamber according to claim 4, characterized in that, The main body of the support plate includes an inner plate and an outer plate arranged in parallel, and the actuator and the actuating crank are both located between the inner plate and the outer plate.

6. The composite support plate for a variable cycle engine combustion chamber according to claim 5, characterized in that, The outer plates of the multiple main body parts are circumferentially fixed and assembled to form an outer cylindrical structure, and the inner plates of the multiple main body parts are circumferentially fixed and assembled to form an inner cylindrical structure; the radial support plate is radially fixed and penetrates the outer cylindrical structure and the inner cylindrical structure.

7. The composite support plate for a variable cycle engine combustion chamber according to claim 1, characterized in that, The maximum outward rotation angle of the front edge of the support plate is 12. o .

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