Adjustable flame stabilizer device and turbine engine afterburner

Abstract

The present invention discloses an adjustable flame stabilizer device, comprising an actuating motor, a connecting structure assembly, and a flame stabilizer assembly. The flame stabilizer assembly includes a flame stabilizer and two movable side walls. The connecting structure assembly connects the actuating motor and the movable side walls, respectively. A combustion stabilizing fuel manifold extends within the flame stabilizer. A direct-injection nozzle is provided on the spray rod of the combustion stabilizing fuel manifold. The outlet of the direct-injection nozzle corresponds to the inner wall surface of the flame stabilizer side wall. The present invention also discloses a turbine engine afterburner combustion chamber. The present invention adopts an adjustable flame stabilizer solution, and by controlling the movable outer wall to be positioned at different gears, it is suitable for use in small-sized turbine engines under different afterburner operating conditions.

Description

Technical Field

[0001] The present invention relates to an auxiliary device inside a turbine engine, in particular to an adjustable flame stabilizer device and a turbine engine afterburner, belonging to the technical field of turbine engines. Background Art

[0002] Turbine engines using afterburners can achieve high thrust in a short period of time. The afterburner typically operates for a relatively short time, lasting between 5 and 30 minutes. For small-scale aircraft like drones and cruise missiles, the afterburner only operates continuously for a few minutes at a time, with the remainder of the time operating in a non-afterburner mode.

[0003] The afterburner, located behind the turbine components, experiences high gas velocity and low pressure. To achieve complete combustion of the high-temperature, high-velocity gas flow with the fresh fuel, a blunt body or flame stabilizer is installed behind the diffuser to create a vortex zone that supports stable combustion and is designed to match the afterburner fuel. Currently, there are numerous aerodynamic layouts for afterburners, with their core components, the fuel supply system (fuel manifold and injection rods), and the flame stabilizer, all of which are fixed structures. Afterburners are moving toward an integrated design to minimize flow resistance losses within the afterburner.

[0004] In summary, existing afterburner technology is directly applied to small-sized turbine engines. While the afterburner chamber size is significantly smaller than that of a Daihatsu afterburner, the aerodynamic parameters are comparable to those of large turbine engines. This makes it difficult to balance flow losses in the afterburner under non-afterburner conditions with combustion efficiency under afterburner conditions. Furthermore, afterburner chambers suffer from a narrow ignition-extinguishing margin. Therefore, there is an urgent need for an afterburner chamber that achieves low flow losses in non-afterburner conditions, high combustion efficiency under afterburner conditions, and excellent ignition and combustion stability. Summary of the Invention

[0005] The purpose of the present invention is to provide an adjustable flame stabilizer device to solve the problem in the prior art that it is difficult to compromise between large flow losses in non-afterburner conditions, high combustion efficiency in afterburner conditions, and good ignition and combustion stability performance in the afterburner combustion chamber of a small and medium-sized turbine engine.

[0006] The present invention is specifically achieved in this way:

[0007] An adjustable flame stabilizer device includes an actuating motor, a connecting structure assembly, and a flame stabilizer assembly. The flame stabilizer assembly includes a flame stabilizer and two movable side walls. The connecting structure assembly is respectively connected to the actuating motor and the movable side walls. A combustion stabilizing fuel main pipe is extended inside the flame stabilizer. A direct-injection nozzle is provided on the injection rod of the combustion stabilizing fuel main pipe. The outlet of the direct-injection nozzle corresponds to the inner wall surface of the flame stabilizer side wall.

[0008] A further approach is:

[0009] The flame stabilizer is a V-shaped flame stabilizer, which is located at the outlet end of the flow channel in the diffuser assembly.

[0010] A further approach is:

[0011] When the actuator motor is in the first gear, the movable side wall is entirely located outside the flame stabilizer, and the flame stabilizer assembly is in the form of a simple V-shaped flame stabilizer. When the actuator motor is in the second gear, only a portion of the movable side wall is located outside the flame stabilizer, and the flame stabilizer assembly forms a double V-shaped flame stabilizer.

[0012] A further approach is:

[0013] The inner wall surface of the end of the V-shaped flame stabilizer is an arc surface, which is beneficial to the interaction between the fuel film and the air.

[0014] A further approach is:

[0015] The outer wall surface of the front end of the movable side wall is an arc surface, which is beneficial to reducing flow resistance.

[0016] The present invention also provides a turbine engine afterburner combustion chamber having an adjustable flame stabilizer device, further comprising a diffuser assembly, an afterburner cylinder, and a fuel supply assembly. The diffuser assembly is located behind the turbine component, and the afterburner cylinder is located behind the diffuser assembly. The two constitute the combustion area of ​​the afterburner combustion chamber, providing the required space for the mixed combustion of high-temperature, high-speed, low-pressure combustion gas and fresh fuel. The fuel supply assembly includes a fuel supply system consisting of an afterburner fuel manifold and a stabilizing fuel manifold. The afterburner fuel manifold is located within the flow channel of the diffuser assembly and in front of the flame stabilizer assembly. The stabilizing fuel manifold consists of a segmented annular pipe and a spray rod, wherein the segmented annular pipe is located outside the afterburner cylinder, and the spray rod is located inside the flame stabilizer. The adjustable flame stabilizer device includes an actuator motor and a flame stabilizer assembly. The flame stabilizer assembly is located at the outlet end of the diffuser assembly. The actuator motor is located outside the afterburner cylinder, passes through the afterburner cylinder, and is connected to the flame stabilizer assembly. The flame stabilizer assembly consists of a simple V-shaped flame stabilizer and a movable sidewall.

[0017] A further approach is:

[0018] The afterburner chamber uses 4-12 flame stabilizer assemblies.

[0019] A further approach is:

[0020] The fuel injection rods of the stable combustion fuel main pipe are built into the extended radial flame stabilizer assembly. Each fuel injection rod consists of multiple groups of fuel injection holes. The fuel is sprayed through the fuel injection holes to the inner wall of the V-shaped flame stabilizer, forming a moving oil film on the wall.

[0021] A further approach is:

[0022] Each fuel injection rod of the stable combustion fuel main pipe is composed of 3-6 groups of direct-injection nozzles, with 2 direct-injection nozzles in each group, forming multiple groups of stable combustion duty flame areas along the radial direction, which is conducive to rapid ignition and full combustion of the afterburner.

[0023] A further approach is:

[0024] The included angle between the two direct-injection nozzles on the spray rod is in the range of 100°-150°.

[0025] A further approach is:

[0026] The number of the fuel injection rods of the combustion stabilizing fuel manifold is the same as the number of the outwardly extending radial flame stabilizers.

[0027] When the engine is operating in the non-afterburner mode, the present invention primarily reduces the flow resistance in the afterburner combustion chamber by lowering the flame stabilizer's blockage ratio. Specifically, the movable sidewall of the flame stabilizer overlaps the V-shaped flame stabilizer wall. When the engine enters the afterburner mode, the actuator motor drives the movable sidewall to move obliquely behind the V-shaped flame stabilizer wall, forming a double V-shaped flame stabilizer. This significantly increases the blockage ratio, facilitating the expansion of the recirculation vortex behind the flame stabilizer and promoting the full combustion of the afterburner fuel. Simultaneously, some airflow enters the gap between the V-shaped flame stabilizer and the movable sidewall. Fuel, through the injection holes on the fuel injection rod of the stabilizing fuel manifold, is sprayed onto the inner wall of the V-shaped flame stabilizer, where it moves along the wall to form an oil film. This oil film is then broken and evaporated by the gap flow at the end of the V-shaped flame stabilizer. It then moves with the gap flow and burns in the recirculation zone within the flame stabilizer, acting as a duty flame, which helps expand the ignition-extinguishment boundary and stabilize combustion performance.

[0028] The present invention has at least the following beneficial effects:

[0029] (1) The present invention adopts an adjustable flame stabilizer solution instead of the traditional non-adjustable radial flame stabilizer solution. By controlling the movable outer wall to be in the first gear, the blockage ratio of the flame stabilizer is minimized. This form is more suitable for the use of small-sized turbine engines under non-afterburner working conditions, with smaller flow losses in the afterburner combustion chamber and higher thrust under non-afterburner working conditions.

[0030] (2) The present invention adopts an adjustable flame stabilizer solution. By controlling the movable outer wall to be in the second gear, the flame stabilizer is blocked to the maximum. This form is more suitable for use under the afterburner working conditions of small-sized turbine engines. It is beneficial for the afterburner combustion chamber to construct a vortex zone and a low-speed zone of sufficiently large size under high-speed and low-pressure conditions, and the afterburner combustion chamber has higher stable combustion performance and combustion efficiency.

[0031] (3) In the present invention, the stable combustion fuel manifold is built into the flame stabilizer and is integrated with the adjustable flame stabilizer in the second gear state. This form is used for small-sized turbine engines and does not increase aerodynamic resistance. It can not only build a recirculation zone of sufficient size, but also control the oil-gas ratio and temperature of the recirculation zone after matching with the fuel, forming a duty flame with the function of a long-burning lamp. This duty flame can ignite the mainstream fresh oil-gas mixture. Because there are multiple injection points in the radial direction of the flame stabilizer, not only the ignition and extinguishing boundaries of the small-sized turbine engine are widened, but also the ignition time is greatly shortened and the combustion efficiency is higher.

[0032] In general, the present invention no longer adopts a fixed flame stabilizer design scheme, but innovatively adopts an adjustable flame stabilizer design scheme. Under non-afterburner conditions, the flame stabilizer has relatively small blockage and small flow loss. Through adjustment by the actuator motor, the flame stabilizer adjusted under processing conditions has relatively large blockage, which can improve combustion efficiency. Secondly, the stable combustion fuel oil circuit and the adjustable flame stabilizer are innovatively integrated into a design. The spray rod sprays fuel onto the inner wall of the flame tube to form a liquid film. Under the impact of the high-speed airflow between the wall and the side wall of the flame stabilizer, the fuel is atomized and mixed with the air, and enters the flame stabilization zone on duty in the flame stabilizer, which greatly widens the ignition and extinguishing boundary of the afterburner combustion chamber and improves the combustion stability of the afterburner combustion chamber. In this way, the comprehensive performance of the afterburner combustion chamber of the small turbine engine is better. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A schematic diagram of the overall layout of the afterburner of the present invention;

[0034] Figure 2 This is a cross-sectional view of the adjustable flame stabilizer of the present invention in the first gear position;

[0035] Figure 3 This is a cross-sectional view of the adjustable flame stabilizer of the present invention in the second gear position;

[0036] Figure 4 A simplified structural diagram of the fuel injection rod of the combustion stabilization fuel manifold assembly of the present invention;

[0037] Figure 5 This is a cross-sectional view of the fuel injection rod of the over-stable fuel manifold of the present invention;

[0038] Figure 6This is a cross-sectional view of the matching of the fuel injection rod and the flame stabilizer of the stable combustion fuel manifold of the present invention;

[0039] Figure numerals: 1. Diffuser assembly; 2. Afterburner cylinder; 3. Fuel supply assembly; 4. Adjustable flame stabilizer device; 11. Diffuser casing; 12. Inner cone; 31. Afterburner fuel main pipe; 32. Stable combustion fuel main pipe; 321. Direct injection nozzle; 322. Injection rod; 41. Actuating motor; 42. Connecting structure assembly; 421. Actuating ring; 422. Actuating rod; 423. Support rod; 43. Flame stabilizer assembly; 431. Flame stabilizer; 432. Movable side wall; 433. Support rod; 434. Hinge; F. Fuel. DETAILED DESCRIPTION

[0040] In order for those skilled in the art to better understand the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and the following embodiments.

[0041] like Figure 1As shown, a device for use in a small turbojet engine afterburner combustion chamber includes a diffuser assembly 1, an afterburner cylinder 2, a fuel supply assembly 3, and an adjustable flame stabilizer device 4. The diffuser assembly 1 includes a diffuser casing 11 and an inner cone 12; the afterburner cylinder 2 is located behind the diffuser assembly 1 and is connected to the diffuser assembly 1 by screws. The cavity formed by the diffuser assembly 1 and the afterburner cylinder 2 provides the required space for the mixed combustion of fuel and gas. The fuel supply assembly 3 includes an afterburner fuel manifold 31 and a stabilizing fuel manifold 32, wherein the afterburner fuel manifold 31 is located in the flow channel of the diffuser assembly 1; the stabilizing fuel manifold 32 is composed of a direct-injection nozzle 321 and a spray rod 322, wherein the direct-injection nozzle 321 is located outside the afterburner cylinder 2 and is a segmented annular pipe, and the spray rod 322 is located inside the flame stabilizer assembly 43 and fixed to the afterburner cylinder 2. The adjustable flame stabilizer device includes an actuating motor 41, a connecting structure assembly 42, and a flame stabilizer assembly 43, wherein the connecting structure assembly includes an actuating ring 421, an actuating rod 422, and a support rod 423, and the flame stabilizer assembly 43 includes a flame stabilizer 431 and two movable side walls 432; the actuating motor 41 is located outside the booster cylinder 2, and the connecting structure assembly 42 connects the actuating motor 41 and the movable side walls 432 of the flame stabilizer, one end of the flame stabilizer 431 is connected to the diffuser casing 11 through a hinged connection, and the other end is fixed to the inner cone 12 of the diffuser assembly through a hinged connection, thereby realizing reliable fixation of the V-shaped flame stabilizer 431; in this embodiment, there is a support rod 423 structure on the outside of the movable side wall 432, and this support rod 423 passes through the booster cylinder 2 and is fixedly connected to the actuating rod 422, and at the same time, the booster cylinder 2 is slotted at the corresponding position for the movable side wall 432 to move. The number of actuator rods 422, support rods 423, and movable side walls 432 corresponds one to one, and the number of flame stabilizers corresponds one to one to the number of fuel injection rods of the stable combustion fuel main pipe. In a common afterburner, 4-12 flame stabilizer assemblies can be used.

[0042] like Figure 2 As shown, this embodiment provides a combination of a V-shaped flame stabilizer 431 and a movable sidewall 432 in an adjustable flame stabilizer device. Specifically, in the non-afterburner operating condition, the output rod of the actuating motor 41 moves to the left, driving the actuating rod 422 and the support rod 423 to the left to their limit position. At this point, the support rod 423 moves along a predetermined groove, causing the movable sidewall 432 to abut against the sidewall of the V-shaped flame stabilizer 431.

[0043] like Figure 3 As shown, in the force-added working condition, the output rod of the actuator motor 41 moves to the right, pulling the actuator rod 422 and the support rod 423 to move to the right to the extreme position. The support rod 423 moves along the preset groove so that the movable side wall 432 moves away from the V-shaped flame stabilizer 431. There is a gap between the movable side wall 432 and the outer wall of the V-shaped flame stabilizer 431, through which the gas A can pass.

[0044] like Figure 4-Figure 5 As shown, based on Examples 1 and 2, the combustion stabilization fuel manifold consists of a segmented annular pipe and 6-10 spray rods 322. The segmented annular pipe is fixed to the outer wall of the afterburner cylinder. The spray rods 322 are located inside the V-shaped flame stabilizer 431 and fixed to the afterburner cylinder 2. The annular pipe and the spray rods 322 are connected by a tee structure. The number of spray rods in the combustion stabilization fuel manifold is the same as the number of extended radial flame stabilizers. The spray rods 322 include 3-6 groups of direct nozzles 321, each group consisting of two direct nozzles 321, and the angle between the two direct nozzles ranges from 100° to 150°.

[0045] like Figure 6 As shown, when the movable side wall 432 moves backward, there is a gap between the side wall of the flame stabilizer 431 and the movable side wall 432, and the fuel gas A can form a stable combustion recirculation vortex zone inside the adjustable flame stabilizer device 4 through the gap; then the fuel F is ejected through the direct nozzle 321 on the spray rod 322 of the stable combustion fuel main pipe 32, and the fuel F impacts the inner wall surface of the side wall of the flame stabilizer 431 and moves to form an oil film. At the end of the side wall of the flame stabilizer 431, it is impacted by the high-speed fuel gas A, and the fuel F breaks, evaporates and mixes with the fuel gas A to burn, forming a stable combustion vortex zone to ignite the mainstream oil-gas mixture, expand the ignition boundary of the afterburner and improve combustion efficiency.

[0046] Working Principle: When the engine is operating in the non-afterburner mode, the actuator motor is in the first gear position, and the movable side wall 432 of the flame stabilizer assembly 43 coincides with the wall surface of the flame stabilizer 431, reducing the blockage ratio of the flame stabilizer 431 and significantly reducing the flow resistance in the afterburner combustion chamber. When the engine enters the afterburner mode, the actuator motor shifts from the first gear to the second gear, driving the movable side wall 432 to move diagonally behind the wall surface of the V-shaped flame stabilizer 431. Together, the two form a double V-shaped flame stabilizer 431, significantly increasing the blockage ratio and facilitating the expansion of the recirculation vortex behind the flame stabilizer 431. This allows for more thorough mixing of the fuel F ejected from the afterburner fuel manifold 31, facilitating complete combustion of the afterburner fuel. At the same time, part of the air flow A will enter the gap between the V-shaped flame stabilizer 431 and the movable side wall 432, and the fuel F will be sprayed onto the inner wall of the V-shaped flame stabilizer 431 through the direct nozzle 321 on the spray rod 322 of the stable combustion fuel main pipe 32, and move along the wall to form an oil film. It will be broken and evaporated by the gap flow A at the end of the V-shaped flame stabilizer 431, and will move with the gap flow A and burn in the recirculation zone inside the flame stabilizer 431, playing the role of a duty flame, which is beneficial to expanding the ignition boundary and improving combustion stability.

[0047] Although the present invention is described herein with reference to illustrative embodiments of the present invention, the above embodiments are merely preferred embodiments of the present invention, and the embodiments of the present invention are not limited to the above embodiments. It should be understood that those skilled in the art can design many other modifications and implementations, which will fall within the scope and spirit of the principles disclosed in this application.

Claims

1. An adjustable flame stabilizer device, characterized in that: It includes an actuating motor, a connecting structure assembly, and a flame stabilizer assembly. The flame stabilizer assembly includes a flame stabilizer and two movable side walls. The connecting structure assembly includes an actuating ring, an actuating rod, and a support rod. The connecting structure assembly is respectively connected to the actuating motor and the movable side walls. A stable combustion fuel main pipe is extended inside the flame stabilizer. A direct-injection nozzle is provided on the injection rod of the stable combustion fuel main pipe. The outlet of the direct-injection nozzle corresponds to the inner wall surface of the flame stabilizer side wall. In the non-afterburner working condition, the actuating motor is in the first gear position, and the output rod of the actuating motor moves to the left, driving the actuating rod and the support rod to move to the left to the limit. Position, the movable side walls are all located outside the flame stabilizer, the flame stabilizer assembly is a V-shaped flame stabilizer, the support rod moves along the preset groove so that the movable side walls are close to the side wall surface of the flame stabilizer; in the afterburner condition, the actuator motor is in the second gear, the actuator motor output rod moves to the right, pulling the actuator rod and the support rod to the right to the extreme position, the support rod moves along the preset groove to move the movable side wall away from the flame stabilizer, there is a gap between the movable side wall and the outer wall of the flame stabilizer, only part of the movable side wall is located outside the flame stabilizer, and the flame stabilizer assembly forms a double V-shaped flame stabilizer.

2. The adjustable flame stabilizer device according to claim 1, characterized in that: The inner wall surface of the end of the V-shaped flame stabilizer is an arc surface, and the outer wall surface of the front end of the movable side wall is also an arc surface.

3. A turbine engine afterburner, characterized in that: The adjustable flame stabilizer device according to claim 1 or 2 further includes a diffuser assembly, an afterburner cylinder, and a fuel supply assembly, wherein the diffuser assembly is located behind the turbine component, the afterburner cylinder is located behind the diffuser assembly, and the two constitute the combustion area of ​​the afterburner combustion chamber; the fuel supply assembly includes a fuel supply system consisting of an afterburner fuel manifold and a stabilizing fuel manifold, the afterburner fuel manifold is located in the flow channel inside the diffuser assembly and in front of the flame stabilizer assembly; the stabilizing fuel manifold is composed of a segmented annular pipe and a spray rod, wherein the segmented annular pipe is located outside the afterburner cylinder, and the spray rod is placed inside the flame stabilizer; The flame stabilizer assembly is located at the outlet end of the diffuser assembly, and the actuating motor is located outside the afterburner cylinder, passes through the afterburner cylinder, and is connected to the flame stabilizer assembly.

4. The turbine engine afterburner according to claim 3, characterized in that: The afterburner chamber uses 4-12 flame stabilizer assemblies.

5. The turbine engine afterburner according to claim 3, characterized in that: The fuel injection rods of the stable combustion fuel main pipe are built into the extended radial flame stabilizer assembly. Each fuel injection rod consists of multiple groups of fuel injection holes. The fuel is sprayed through the fuel injection holes to the inner wall of the V-shaped flame stabilizer, forming a moving oil film on the wall.

6. The turbine engine afterburner according to claim 5, characterized in that: Each fuel injection rod of the stable combustion fuel main pipe is composed of 3-6 groups of direct-injection nozzles, with 2 direct-injection nozzles in each group, forming multiple groups of stable combustion duty flame areas along the radial direction.

7. The turbine engine afterburner according to claim 6, characterized in that: The included angle between the two direct-injection nozzles on the spray rod is in the range of 100°-150°.

8. The turbine engine afterburner according to claim 7, characterized in that: The number of the fuel injection rods of the combustion stabilizing fuel manifold is the same as the number of the outwardly extending radial flame stabilizers.

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