A rotating strut structure for a gas turbine augmented ram combined engine

Abstract

The application discloses a rotating support plate structure for a gas turbine augmented ram combined engine, the gas turbine augmented ram combined engine comprising an isolated section and a combustion chamber in communication with each other, and a gas turbine assembly arranged axially in the combustion chamber, the rotating support plate structure being arranged in the combustion chamber and comprising: an annular rotating seat rotatable along the axis of the combustion chamber, the rotating seat being uniformly provided with a plurality of rotatable support plates in the circumferential direction; and a plurality of fixed support plates uniformly arranged in the circumferential direction of the gas turbine assembly, the number of the fixed support plates being the same as that of the rotatable support plates. The rotating support plate structure is further provided with a rotating motor and a rotating shaft coaxial with the axis of the combustion chamber, the rotating motor being located in the gas turbine assembly, one end of the rotating shaft being connected with the rotating motor, and the other end of the rotating shaft penetrating through the gas turbine assembly and being inserted into the rotating seat. The application can realize the adjustment of the blockage ratio through the rotating support plate, meet the blockage ratio required by different working conditions of the engine, and ensure high combustion efficiency in each working condition.

Description

Technical Field

[0001] This invention relates to the field of combined engine technology, and in particular to a rotating support structure for a gas turbine-enhanced ramjet combined engine. Background Technology

[0002] The gas turbine-enhanced rocket ramjet combined engine is a combined engine that organically integrates a ramjet engine and an air-turbine rocket engine (ATR). It can activate different optimal operating modes at different flight altitudes and Mach numbers, fully utilizing the characteristics of both the ATR and ramjet engines. During operation, the gas turbine-enhanced rocket ramjet combined engine typically uses the ATR mode in the low-speed range and the ramjet mode in the high-speed range. The ramjet mode is further divided into low-Mach and high-Mach scenarios.

[0003] For gas turbine-enhanced rocket ramjet engines, the required shut-off ratio varies depending on the operating condition to improve combustion efficiency. In ATR mode, compared to turbofan engines, the combustion chamber structure is more compact and has a shorter axial length, but the airflow velocity is higher. Therefore, in the low-speed ATR mode, it is necessary to enhance the uniform mixing of the bypass air and the fuel-rich internal combustion gases to improve combustion efficiency. In the low Mach of the ramjet mode, the influent total temperature and combustion chamber pressure are lower, requiring enhanced mixing and a higher shut-off ratio to improve combustion efficiency. In the high Mach of the ramjet mode, the influent total temperature and combustion chamber pressure are higher, making combustion easier. Therefore, in the high Mach ramjet range, it is necessary to reduce the shut-off ratio to ensure combustion efficiency while minimizing combustion chamber flow resistance.

[0004] In existing technologies, engines typically use fixed support plate structures for combustion flame stabilization and fuel injection. However, since the number and position of the fixed support plates are fixed, they can only provide a fixed combustion chamber blockage ratio and fuel injection position. Gas turbine enhanced rocket ramjet combined engine cannot simultaneously meet the blockage ratio required to ensure high combustion efficiency in three conditions: low-speed ATR mode, low Mach ramjet mode, and high Mach ramjet mode. Summary of the Invention

[0005] Therefore, it is necessary to provide a rotating support plate structure for a gas turbine-enhanced ramjet combined engine to address the above-mentioned technical problems. The rotation of the support plate can adjust the blockage ratio to meet the blockage ratio requirements of different engine operating conditions, thus ensuring high combustion efficiency under various operating conditions.

[0006] This invention provides a rotating support structure for a gas turbine-enhanced ramjet combined engine. The gas turbine-enhanced ramjet combined engine includes an interconnected isolation section and a combustion chamber. A gas turbine assembly is axially disposed within the combustion chamber. The rotating support structure is disposed within the combustion chamber and includes:

[0007] An annular rotating seat that can rotate along the axis of the combustion chamber, with multiple rotatable support plates evenly assembled around the circumference of the rotating seat;

[0008] Multiple fixed supports, the same number as the number of rotatable supports, are uniformly assembled along the circumference of the gas turbine assembly.

[0009] In one embodiment, the rotating support plate structure is further provided with a rotating motor and a rotating shaft whose axis coincides with the axis of the combustion chamber;

[0010] The rotary motor is located inside the gas turbine assembly. One end of the rotating shaft is connected to the rotary motor, and the other end of the rotating shaft passes through the gas turbine assembly and is inserted into the rotating base.

[0011] In one embodiment, one end of the fixed support plate is fixedly connected to the inner wall of the combustion chamber, and the other end of the fixed support plate is fixedly connected to the gas turbine assembly.

[0012] One end of the rotatable support plate is fixedly connected to the rotating seat, while the other end of the rotatable support plate is suspended in the air.

[0013] In one embodiment, both the rotatable support plate and the fixed support plate include a wedge-shaped portion, a straight portion, and a lobe portion connected sequentially along the direction from the isolation section to the combustion chamber.

[0014] The interior of the wedge of the rotatable support plate is provided with a fuel through hole along the axial direction. The combustion chamber is provided with a feed inlet. The fuel through hole is connected to the feed inlet. The inclined surface of the wedge of the rotatable support plate is provided with multiple fuel injection holes. The fuel injection holes are connected to the fuel through hole.

[0015] Each rotatable and fixed support plate has a gas passage hole in the axial direction inside its straight section. The inlet end of the gas passage hole of the fixed support plate is connected to the gas turbine assembly, and the inlet end of the gas passage hole of the rotatable support plate is connected to the rotating seat.

[0016] Each rotatable support plate and fixed support plate has several lobe structures in its lobe section. Each lobe structure has a gas outlet on the side away from the straight section, and the gas outlet is connected to the gas through hole.

[0017] In one embodiment, both the rotatable support plate and the fixed support plate are tilted toward the isolation section at the same angle, which is 45° to 60°.

[0018] In one embodiment, the number of rotatable support plates and fixed support plates is 4 to 12.

[0019] In one embodiment, the gas turbine-enhanced ramjet combined engine is provided with an annular fixed baffle, a movable baffle, and a guide vane. The gas turbine assembly is provided with a conical housing, and the fixed baffle and the guide vane are both located between the fixed baffle and the housing.

[0020] The opening radius of the fixed baffle facing the shell is equal to the axial radius of the movable baffle and the bottom axial radius of the shell;

[0021] The deflector is frustum-shaped, and the bottom radius of the deflector is equal to the axial radius of the movable baffle.

[0022] The bottom of the deflector is fixedly connected to the bottom of the housing, and the fixed support plate is set on the outer side of the top of the housing;

[0023] One end of the movable baffle abuts against the fixed baffle along the axis, and the other end abuts against the bottom of the housing. The movable baffle can move along its own axis.

[0024] In one embodiment, a compressor is provided in the isolation section, a turbine and a gas generator are provided inside the housing, and the rotating seat is frustum-shaped, with the bottom of the rotating seat abutting and communicating with the top of the housing.

[0025] The beneficial effects of this invention are:

[0026] (1) In this invention, the rotating seat can be rotated by the rotating shaft connected to the rotating motor, which drives multiple rotatable support plates and multiple fixed support plates to be staggered or overlapped in the direction of the combustion chamber axis. In the low speed section ATR mode and the low Mach condition of the stamping mode, the rotatable support plates and the fixed support plates are staggered, which increases the blockage ratio of the combustion chamber, thereby enhancing mixing and improving combustion efficiency. In the high Mach condition of the stamping mode, the rotatable support plates and the fixed support plates are overlapped, which can effectively reduce the blockage ratio of the combustion chamber, ensure combustion efficiency, and reduce the flow resistance loss of the combustion chamber.

[0027] (2) Both the rotatable support plate and the fixed support plate of the present invention are provided with several lobe structures. The lobe structures can generate flow vortices, thereby enhancing the mixing of incoming air or fuel-rich gas with fuel and further improving combustion efficiency. Attached Figure Description

[0028] Figure 1 A schematic diagram of the rotating support plate structure provided in an embodiment of the present invention assembled in a gas turbine-enhanced ramjet combined engine;

[0029] Figure 2 for Figure 1 One of the schematic diagrams of the cross-sectional structure along the central axis;

[0030] Figure 3 This is a schematic diagram showing the assembly relationship between the rotatable support plate and the fixed support plate, the housing, and the rotating seat provided in an embodiment of the present invention.

[0031] Figure 4 This is a schematic diagram of the structure when the rotatable support plate and the fixed support plate are intersected.

[0032] Figure 5 This is a schematic diagram of the structure when the rotatable support plate and the fixed support plate overlap.

[0033] Figure 6 This is a schematic diagram of the structure of the rotatable support plate provided in an embodiment of the present invention;

[0034] Figure 7 for Figure 6 A structural diagram from another angle.

[0035] Explanation of reference numerals in the attached drawings: 100, isolation section; 200, combustion chamber; 300, rotating seat; 310, rotatable support plate; 320, fixed support plate; 330, rotating shaft; 400, wedge-shaped part; 410, straight part; 420, lobe part; 430, lobe structure; 440, fuel through hole; 450, fuel injection hole; 460, gas outlet; 470, feed inlet; 500, fixed baffle; 600, movable baffle; 700, guide plate; 800, shell; 900, rotary motor. Detailed Implementation

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

[0037] It should be noted that in the description of this invention, "upper," "lower," "top," "bottom," and orientation or positional relationship are based on the appendix. Figure 1 The orientations or positional relationships shown are for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0038] In one embodiment, such as Figure 1 , Figure 2 and Figure 3 As shown in this embodiment, a rotating support structure for a gas turbine-enhanced ramjet combined engine is provided. The gas turbine-enhanced ramjet combined engine includes an interconnected isolation section 100 and a combustion chamber 200. A gas turbine assembly is axially disposed within the combustion chamber 200. The rotating support structure is disposed within the combustion chamber 200 and includes:

[0039] An annular rotating seat 300, rotatable along the axis of combustion chamber 200, is provided with multiple rotatable support plates 310 evenly mounted circumferentially on the rotating seat 300. Multiple fixed support plates 320, the same number as the rotatable support plates 310, are also evenly mounted circumferentially on the gas turbine assembly. The rotating support plate structure also includes a rotary motor 900 and a rotating shaft 330 whose axis coincides with the axis of combustion chamber 200. The rotary motor 900 is located inside the gas turbine assembly, one end of the rotating shaft 330 is connected to the rotary motor 900, and the other end of the rotating shaft 330 passes through the gas turbine assembly and is inserted into the rotating seat 300.

[0040] In this embodiment, the rotating seat 300 can be controlled to rotate by the rotating shaft 330, thereby driving the multiple rotatable support plates 310 mounted on the rotating seat 300 to rotate.

[0041] During rotation, the rotatable support plate 310 can form an interleaved or overlapping state with the fixed support plate 320 along the axis of the combustion chamber 200, enabling control of the blockage ratio of the combustion chamber 200. When the combined engine is operating at low speeds in ATR mode and ramjet mode (low Mach), rotating the rotatable support plate 310 to interleave with the fixed support plate 320 increases the blockage ratio of the combustion chamber 200, enhancing the mixing of incoming air or fuel-rich combustion gases with the fuel, further improving combustion efficiency. When the combined engine is operating at high Mach in ramjet mode, rotating the rotatable support plate 310 to overlap with the fixed support plate 320, at which point the blockage ratio of the combustion chamber 200 is minimized, enhancing combustion efficiency under this condition.

[0042] It is worth noting that when the rotatable support plate 310 and the fixed support plate 320 are staggered, and any one of the rotatable support plates 310 is located in the middle of the angle between the two fixed support plates 320 along the axis of the combustion chamber 200, the blockage ratio is the largest and the combustion efficiency is the highest in the low speed ATR mode and the low Mach condition of the ramming mode.

[0043] It should be noted that in this embodiment, the Mach number in the low-speed ATR mode is Ma0-Ma3, the Mach number in the low-Mach condition of the stamping mode is Ma3-Ma4, and the Mach number in the high-Mach condition of the stamping mode is Ma5-Ma6.

[0044] In one embodiment, one end of the fixed support plate 320 is fixedly connected to the inner wall of the combustion chamber 200, and the other end of the fixed support plate 320 is fixedly connected to the gas turbine assembly; one end of the rotatable support plate 310 is fixedly connected to the rotating seat 300, and the other end of the rotatable support plate 310 is suspended.

[0045] The length of the fixed support plate 320 is less than the length of the rotatable support plate 310. Both the rotatable support plate 310 and the fixed support plate 320 are inclined towards the isolation section 100 at the same angle, which is 45° to 60°. The number of rotatable support plates 310 and fixed support plates 320 is 4 to 12.

[0046] Specifically, in this embodiment, the tilt angle is 45°, and there are 8 rotatable support plates 310 and 8 fixed support plates 320.

[0047] The staggered state of the rotatable support plate 310 and the fixed support plate 320 is as follows: Figure 4 As shown, the overlapping state of the rotatable support plate 310 and the fixed support plate 320 is as follows: Figure 5 As shown.

[0048] In one embodiment, such as Figure 6 and Figure 7 As shown, both the rotatable support plate 310 and the fixed support plate 320 include a wedge portion 400, a straight portion 410 and a lobed portion 420 connected sequentially along the direction from the isolation section 100 to the combustion chamber 200.

[0049] The interior of the wedge portion 400 of the rotatable support plate 310 is provided with a fuel through hole 440 along the axial direction. The combustion chamber 200 is provided with a feed inlet 470. The fuel through hole 440 is connected to the feed inlet 470. The inclined surface of the wedge portion 400 of the rotatable support plate 310 is provided with a plurality of fuel injection holes 450. The fuel injection holes 450 are connected to the fuel through hole 440.

[0050] External fuel enters the fuel through-hole 440 through the feed port 470, and is then injected into the combustion chamber 200 through the fuel injection port 450. It should be noted that the fuel through-hole 440 is an open-end and sealed-end through-hole.

[0051] Each rotatable support plate 310 and fixed support plate 320 has a gas passage hole arranged axially inside its straight portion 410. The inlet end of the gas passage hole of the fixed support plate 320 is connected to the gas turbine assembly, and the inlet end of the gas passage hole of the rotatable support plate 310 is connected to the rotating seat 300. It should be noted that the gas passage hole is also a through hole with one end open and the other end sealed.

[0052] Each rotatable support plate 310 and fixed support plate 320 has a number of lobe structures 430 on its lobe portion 420. Each lobe structure 430 has a gas outlet 460 on the side away from the straight portion 410. The gas outlet 460 is connected to the gas through hole.

[0053] In ATR mode, the fuel-rich gas generated by the gas turbine assembly first enters the gas through-hole, and then exits from the gas outlet 460 on the lobe structure 430 into the combustion chamber 200.

[0054] In this embodiment, the lobe structure 430 can generate a flow vortex, thereby enhancing the mixing of incoming air or fuel-rich gas with the fuel and further improving combustion efficiency.

[0055] In one embodiment, the gas turbine-enhanced ramjet combined engine is provided with an annular fixed baffle 500, a movable baffle 600 and a guide vane 700 inside, and the gas turbine assembly is provided with a conical housing 800. The fixed baffle 500 and the guide vane 700 are both located between the fixed baffle 500 and the housing 800.

[0056] The opening radius of the fixed baffle 500 facing the housing 800 is equal to the axial radius of the movable baffle 600 and the bottom axial radius of the housing 800; the guide plate 700 is frustoconical, and the bottom radius of the guide plate 700 is equal to the axial radius of the movable baffle 600; the bottom of the guide plate 700 is fixedly connected to the bottom of the housing 800, and the fixed support plate 320 is disposed on the outer side of the top of the housing 800; one end of the movable baffle 600 abuts against the fixed baffle 500 along its axis, and the other end abuts against the bottom of the housing 800, and the movable baffle 600 can move along its own axis.

[0057] In the ramjet mode, the movable baffle 600 abuts against the fixed baffle 500 at one end along its axis and against the bottom of the housing 800 at the other end. Incoming air flows outside the fixed baffle 500, the movable baffle 600, and the housing 800, mixing with fuel injected from the fuel nozzle of the movable baffle 600 before entering the combustion chamber 200 for co-combustion. In the ATR mode, the movable baffle 600 is slid to the right towards the combustion chamber 200 until the movable baffle 600 and the guide vane 700 no longer overlap radially in the combustion chamber 200. At this point, the compressed air enters the outer flow channel of the housing 800 along the guide vane 700, mixing with fuel injected from the fuel nozzle of the movable baffle 600 and flammable gas injected from the gas outlet 460 before entering the combustion chamber 200 for co-combustion.

[0058] Specifically, a compressor is installed within the isolation section 100, and a turbine and a gas generator are installed inside the housing 800. The rotating seat 300 is frustum-shaped, with its bottom abutting and communicating with the top of the housing 800. Fuel-rich gas can be transferred from inside the housing 800 to the rotating seat 300. Both the housing 800 and the rotating seat 300 have gas inlets that communicate with gas through holes. In this embodiment, auxiliary rotation components are provided between the rotating seat 300 and the housing 800 to prevent friction from causing the rotation to stop.

[0059] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A rotating support plate structure for a gas turbine-enhanced ramjet combined engine, characterized in that, The gas turbine-enhanced ramjet combined engine includes an interconnected isolation section (100) and a combustion chamber (200). A gas turbine assembly is axially disposed within the combustion chamber (200). A rotating support structure is disposed within the combustion chamber (200), and the rotating support structure includes: An annular rotating seat (300) that can rotate along the axis of the combustion chamber (200) is provided, and the rotating seat (300) is uniformly equipped with a plurality of rotatable support plates (310) in the circumferential direction; A plurality of fixed support plates (320) are uniformly assembled along the circumference of the gas turbine assembly, the same number as the number of the rotatable support plates (310); The rotating support plate structure is also provided with a rotating motor (900) and a rotating shaft (330) whose axis coincides with the axis of the combustion chamber (200). The rotary motor (900) is located inside the gas turbine assembly. One end of the rotating shaft (330) is connected to the rotary motor (900), and the other end of the rotating shaft (330) passes through the gas turbine assembly and is inserted into the rotating seat (300). One end of the fixed support plate (320) is fixedly connected to the inner wall of the combustion chamber (200), and the other end of the fixed support plate (320) is fixedly connected to the gas turbine assembly; One end of the rotatable support plate (310) is fixedly connected to the rotating seat (300), and the other end of the rotatable support plate (310) is suspended. Both the rotatable support plate (310) and the fixed support plate (320) include a wedge-shaped part (400), a straight part (410), and a lobe part (420) connected sequentially along the direction from the isolation section (100) to the combustion chamber (200); The interior of the wedge portion (400) of the rotatable support plate (310) is provided with a fuel through hole (440) along the axial direction. The combustion chamber (200) is provided with a feed inlet (470). The fuel through hole (440) is connected to the feed inlet (470). The inclined surface of the wedge portion (400) of the rotatable support plate (310) is provided with a plurality of fuel injection holes (450). The fuel injection holes (450) are connected to the fuel through hole (440). Each of the straight portions (410) of the rotatable support plate (310) and the fixed support plate (320) is provided with a gas passage hole in the axial direction. The inlet end of the gas passage hole of the fixed support plate (320) is connected to the gas turbine assembly, and the inlet end of the gas passage hole of the rotatable support plate (310) is connected to the rotating seat (300). Each of the rotatable support plate (310) and the fixed support plate (320) has a number of lobe structures (430) on its lobe portion (420). Each lobe structure (430) has a gas outlet (460) on the side away from the straight portion (410). The gas outlet (460) is connected to the gas through hole.

2. The rotating support plate structure for a gas turbine-enhanced ramjet combined engine according to claim 1, characterized in that, Both the rotatable support plate (310) and the fixed support plate (320) are inclined toward the isolation section (100) at the same angle, which is 45°~60°.

3. The rotating support plate structure for a gas turbine-enhanced ramjet combined engine according to claim 2, characterized in that, The number of rotatable support plates (310) and fixed support plates (320) are both 4 to 12.

4. The rotating support plate structure for a gas turbine-enhanced ramjet combined engine according to claim 3, characterized in that, The gas turbine-enhanced ramjet combined engine is provided with an annular fixed baffle (500), a movable baffle (600) and a guide plate (700) inside. The turbine assembly is provided with a conical housing (800). The movable baffle (600) and the guide plate (700) are both located between the fixed baffle (500) and the housing (800). The opening radius of the fixed baffle (500) facing the housing (800) is equal to the axial radius of the movable baffle (600) and the bottom axial radius of the housing (800); The guide plate (700) is frustum-shaped, and the bottom radius of the guide plate (700) is equal to the axial radius of the movable baffle (600). The bottom of the guide plate (700) is fixedly connected to the bottom of the housing (800), and the fixed support plate (320) is disposed on the outer side of the top of the housing (800); One end of the movable baffle (600) abuts against the fixed baffle (500) along the axis, and the other end abuts against the bottom of the housing (800). The movable baffle (600) can move along its own axis.

5. The rotating support plate structure for a gas turbine-enhanced ramjet combined engine according to claim 4, characterized in that, An air compressor is installed inside the isolation section (100), and a turbine and a gas generator are installed inside the housing (800); The rotating seat (300) is frustum-shaped, and the bottom of the rotating seat (300) abuts against and communicates with the top of the housing (800).

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