Miniature combustion chamber with regenerative structure

Abstract

The application relates to the technical field of micro-scale combustion, in particular to a micro combustion chamber with a regenerative structure. The micro combustion chamber with the regenerative structure is used for a gas turbine and comprises a fluid passage, the fluid passage can circulate air and fuel, the fluid passage is provided with an outer exhaust passage, an outer ring cavity, a flame tube inner cavity, an inner ring cavity, an inner exhaust passage and a fuel gas collecting cavity, the air flows into the flame tube inner cavity through the outer ring cavity and the inner ring cavity in sequence, the fuel can flow into the flame tube inner cavity through the fuel gas collecting cavity, the air and the fuel are combusted in the flame tube inner cavity to form high-temperature fuel gas, and the high-temperature fuel gas flows into the outer exhaust passage through the inner exhaust passage; the high-temperature fuel gas in the inner exhaust passage and the flame tube inner cavity can exchange heat with the air in the inner ring cavity, and the high-temperature fuel gas in the outer exhaust passage and the flame tube inner cavity can exchange heat with the air in the outer ring cavity. In this way, the air is preheated by the high-temperature fuel gas, the total heat cycle thermal efficiency is improved, and the combustion chamber performance is improved.

Description

Technical Field

[0001] This application relates to the field of microscale combustion technology, and in particular to a micro combustion chamber with a heat recovery structure. Background Technology

[0002] In recent years, micro-devices such as sensors, micro-scale aircraft, and micro-motors, as well as personal portable systems, have been increasingly widely used in defense, scientific research, medical, and industrial fields. This has led to a growing demand for micro-energy systems that are small in size, lightweight, have high energy density, and can be sustainably powered. Typically, micro-devices are powered by chemical batteries such as primary alkaline batteries, rechargeable batteries, and high-performance novel batteries. However, their energy density and power density are low; for example, the energy density of lithium-ion batteries is only one-sixtieth that of hydrocarbon fuels.

[0003] With the development of MEMS technology, micro-power devices based on fuel combustion, such as micro combustion turbines, micro thermoelectric and thermophotovoltaic power generation systems, have broad application prospects due to their combination of high power density and high energy density. However, as the core component of micro-power systems, micro-combustion chambers are affected by scale effects, resulting in problems such as short gas residence time, difficulty in mixing, and incomplete combustion. In addition, the large area-to-volume ratio of micro-combustion chambers exacerbates heat loss and leads to poor flame stability. Summary of the Invention

[0004] The summary of this application introduces a series of simplified concepts, which will be further explained in detail in the detailed description section. This summary is not intended to limit the key features and essential technical features of the claimed technical solution, nor is it intended to determine the scope of protection of the claimed technical solution.

[0005] This application provides a miniature combustion chamber with a heat recovery structure for a gas turbine, comprising:

[0006] A fluid channel, capable of facilitating the flow of air and fuel, is provided with an external exhaust channel, an outer annular cavity, a flame tube inner cavity, an inner annular cavity, an internal exhaust channel, and a fuel collection chamber. The outer annular cavity is located between the external exhaust channel and the flame tube inner cavity, and is spaced apart from both. The inner annular cavity is located between the flame tube inner cavity and the internal exhaust channel, and is spaced apart from both. The fuel collection chamber and the flame tube inner cavity are both located between the inner and outer annular cavities. The outer annular cavity is connected to the inner cavity of the flame tube via the inner annular cavity, and the air flows into the inner cavity of the flame tube successively through the outer annular cavity and the inner annular cavity; the fuel gas collecting cavity is connected to the inner cavity of the flame tube, and the fuel can flow into the inner cavity of the flame tube through the fuel gas collecting cavity; the inner cavity of the flame tube is connected to the outer exhaust channel via the inner exhaust channel, and the air and the fuel are burned in the inner cavity of the flame tube to form high-temperature gas, and the high-temperature gas flows into the outer exhaust channel through the inner exhaust channel; The high-temperature gas in the internal exhaust channel can exchange heat with the air in the inner annular cavity, the high-temperature gas in the external exhaust channel can exchange heat with the air in the outer annular cavity, and the high-temperature gas in the inner cavity of the flame tube can exchange heat with the air in both the inner and outer annular cavities.

[0007] According to this application, a micro combustion chamber with a heat recovery structure is used in a gas turbine. It includes a fluid passage through which air and fuel can flow. The fluid passage is provided with an external exhaust passage, an outer annular cavity, a flame tube inner cavity, an inner annular cavity, an internal exhaust passage, and a fuel collection chamber. The outer annular cavity is located between the external exhaust passage and the flame tube inner cavity, and is spaced apart from both. The inner annular cavity is located between the flame tube inner cavity and the internal exhaust passage, and is spaced apart from both. The fuel collection chamber and the flame tube inner cavity are both located between the inner and outer annular cavities. The outer annular cavity is connected to the flame tube inner cavity through the inner annular cavity. Air flows into the inner cavity of the flame tube successively through the outer and inner annular cavities; the fuel gas collection chamber is connected to the inner cavity of the flame tube, allowing fuel to flow into the inner cavity of the flame tube through the fuel gas collection chamber; the inner cavity of the flame tube is connected to the outer exhaust channel through the inner exhaust channel, where air and fuel burn to form high-temperature gas, which flows into the outer exhaust channel through the inner exhaust channel; the high-temperature gas in the inner exhaust channel can exchange heat with the air in the inner annular cavity, the high-temperature gas in the outer exhaust channel can exchange heat with the air in the outer annular cavity, and the high-temperature gas in the inner cavity of the flame tube can exchange heat with the air in both the inner and outer annular cavities. In this way, the micro-combustion chamber, through the coordination of the outer annular cavity, inner annular cavity, external exhaust channel, and internal exhaust channel, increases the air flow time within the micro-combustion chamber, allowing the high-temperature combustion gas to fully exchange heat with the air, thereby preheating the air, realizing heat recovery and utilization, reducing energy consumption, and improving the overall thermal efficiency of the heat cycle. At the same time, the preheated air enters the inner cavity of the flame tube at a higher initial temperature, which can promote rapid mixing and complete combustion of air and fuel, improve combustion stability, and enhance the performance of the micro-combustion chamber.

[0008] Optionally, the micro combustion chamber with a regenerative structure further includes a casing assembly, which includes an annular cavity channel outer casing and a flame tube outer casing spaced apart. The annular cavity channel outer casing is fitted outside the flame tube outer casing, and the outer annular cavity is located between the annular cavity channel outer casing and the flame tube outer casing.

[0009] Optionally, the casing assembly further includes an annular cavity channel inner casing and a flame tube inner casing spaced apart. The flame tube inner casing is sleeved outside the annular cavity channel inner casing. One end of the flame tube inner casing is connected to one end of the annular cavity channel inner casing, and the other end of the flame tube inner casing is connected to one end of the flame tube outer casing. The other end of the annular cavity channel inner casing is connected to one end of the annular cavity channel outer casing. The flame tube inner cavity is located between the flame tube outer casing and the flame tube inner casing. The inner annular cavity is located between the annular cavity channel inner casing and the flame tube inner casing. The internal exhaust channel is located inside the annular cavity channel inner casing.

[0010] Optionally, the casing assembly further includes an exhaust channel outer casing spaced apart from the annular cavity channel outer casing. The exhaust channel outer casing is sleeved outside the annular cavity channel outer casing, and the other end of the annular cavity channel outer casing is connected to the exhaust channel outer casing. The external exhaust channel is located between the annular cavity channel outer casing and the exhaust channel outer casing.

[0011] Optionally, the micro combustion chamber with a heat recovery structure further includes a fuel inlet, which passes through the outer casing of the exhaust channel and the outer casing of the annular cavity channel and is inserted into the outer casing of the flame tube. The fuel inlet is connected to the fuel collection chamber, and the fuel can flow into the fuel collection chamber through the fuel inlet.

[0012] Optionally, the micro combustion chamber with a heat recovery structure further includes an air inlet and a fuel inlet, which are located at opposite ends of the micro combustion chamber along its axial direction. The air inlet is used to supply air and is connected to the outer annular cavity, allowing the air to flow into the outer annular cavity.

[0013] Optionally, the inner casing of the flame tube is provided with a main combustion port, which penetrates the inner casing of the flame tube, and the inner annular cavity communicates with the inner cavity of the flame tube through the main combustion port; or, the inner casing of the flame tube is provided with a main combustion port and a mixing port spaced apart, both of which penetrate the inner casing of the flame tube, and the inner annular cavity communicates with the inner cavity of the flame tube through the main combustion port and the mixing port.

[0014] Optionally, the casing assembly further includes a first connecting member, the two ends of which are respectively connected to the outer casing of the flame tube and the inner casing of the flame tube, and the first connecting member is located between the inner cavity of the flame tube and the fuel gas collection chamber along the axial direction of the micro combustion chamber.

[0015] Optionally, the first connecting member is provided with an injection hole, the fuel gas collection chamber is connected to the inner cavity of the flame tube through the injection hole, and the fuel in the fuel gas collection chamber flows into the inner cavity of the flame tube through the injection hole; the inner casing of the flame tube is provided with a main combustion hole, and the main combustion hole and the injection hole are arranged opposite each other along the axial direction of the micro combustion chamber.

[0016] Optionally, the exhaust channel outer casing further includes an exhaust port that penetrates the exhaust channel outer casing, through which the high-temperature gas can be discharged. Attached Figure Description

[0017] The following figures are included as part of this application for understanding the application. The figures illustrate embodiments of the application and their descriptions, explaining the apparatus and principles of the application. In the figures, Figure 1 This is a cross-sectional schematic diagram of a micro combustion chamber with a heat recovery structure according to an embodiment of this application; Figure 2 for Figure 1 The diagram shows the flow of air, fuel, and high-temperature combustion gases in a miniature combustion chamber with a regenerating structure.

[0018] Explanation of reference numerals in the attached figures: 1: A miniature combustion chamber with a heat recovery structure; 10: Fluid channels; 11: External exhaust passage; 12: Outer annular cavity; 13: Flame tube inner cavity; 14: Inner annular cavity; 15: Internal exhaust passage; 16: Fuel gas collection cavity; 17: Air; 18: Fuel; 19: High-temperature combustion gas; 20: Casing assembly; 21: Exhaust passage outer casing; 211: Exhaust port; 22: Annular cavity channel outer casing; 23: Flame tube outer casing; 24: Inner casing of the flame tube; 241: Main combustion port; 242: Mixing port; 25: Casing inside the annular cavity channel; 26: First connecting member; 261: Injection hole; 30: Fuel imports; 40: Air inlet; 50: Compressor impeller; 60: Axis; 70: Turbo. Detailed Implementation

[0019] The following description provides numerous specific details to offer a more thorough understanding of this application. However, it will be apparent to those skilled in the art that this application can be practiced without one or more of these details. In other instances, certain technical features well-known in the art have not been described to avoid confusion with this application.

[0020] To fully understand this application, detailed portions will be set forth in the following description in order to illustrate it. Obviously, implementation of this application is not limited to the specific details familiar to those skilled in the art. Preferred embodiments of this application are described in detail below; however, other embodiments may exist besides these detailed descriptions, and should not be construed as being limited to the embodiments set forth herein.

[0021] It should be understood that the terminology used herein is intended only to describe particular embodiments and is not intended to limit the scope of this application. The singular forms “a,” “an,” and “the” are also intended to include the plural forms unless the context clearly indicates otherwise. When the terms “comprising” and / or “including” are used in this specification, they indicate the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or combinations thereof. The terms “upper,” “lower,” “front,” “rear,” “left,” “right,” and similar expressions used in this application are for illustrative purposes only and are not intended to be limiting.

[0022] The ordinal numbers such as "first" and "second" used in this application are merely identifiers and have no other meaning, such as a specific order. In this application, unless otherwise expressly specified and limited, "above" or "below" a second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of a second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" of a second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0023] The specific embodiments of this application will be described in more detail below with reference to the accompanying drawings, which illustrate representative embodiments of this application and are not intended to limit this application.

[0024] like Figure 1 and Figure 2 As shown, this application provides a micro combustion chamber 1 with a heat recovery structure (hereinafter referred to as micro combustion chamber 1), which is used in a gas turbine.

[0025] The micro-combustion chamber 1 with a heat recovery structure includes a fluid passage 10 located inside the micro-combustion chamber 1. Air 17 and fuel 18 can flow through the fluid passage 10.

[0026] For example, the micro-combustion chamber 1 is connected to its external environment, which can supply air 17 into it, allowing the air 17 to flow within the chamber. The micro-combustion chamber 1 can also be connected to a fuel device outside the chamber, which can supply fuel 18 to the fluid channel 10. Optionally, the fuel 18 can be gaseous fuel. Both air and gaseous fuel can flow along a specific path in the fluid channel 10, allowing them to mix and burn, thereby powering the gas turbine. This application does not limit the specific structure of the fuel device outside the micro-combustion chamber 1 or the gas turbine.

[0027] The fluid passage 10 is provided with an external exhaust passage 11, an outer annular cavity 12, a flame tube inner cavity 13, an inner annular cavity 14, an internal exhaust passage 15, and a fuel collection chamber 16. All of these components are located inside the micro-combustion chamber 1. The external exhaust passage 11, outer annular cavity 12, flame tube inner cavity 13, inner annular cavity 14, internal exhaust passage 15, and fuel collection chamber 16 are arranged coaxially. The central axes of all these components coincide.

[0028] Specifically, the external exhaust passage 11 is fitted outside the outer annular cavity 12, and the outer annular cavity 12 is fitted outside the inner cavity 13 of the flame tube. The outer annular cavity 12 is located between the external exhaust passage 11 and the inner cavity 13 of the flame tube along the radial direction of the micro combustion chamber 1, and the outer annular cavity 12 is spaced apart from both the external exhaust passage 11 and the inner cavity 13 of the flame tube.

[0029] The inner cavity 13 of the flame tube is fitted outside the inner annular cavity 14, and the inner annular cavity 14 is fitted outside the inner exhaust passage 15. The inner annular cavity 14 is located between the inner cavity 13 of the flame tube and the inner exhaust passage 15 along the radial direction of the micro combustion chamber 1. The inner annular cavity 14 is connected to the inner cavity 13 of the flame tube and is spaced apart from the inner exhaust passage 15.

[0030] One end of the outer annular cavity 12 is connected to the external environment of the micro-combustion chamber 1, and the other end of the outer annular cavity 12 is connected to the inner annular cavity 14. The micro-combustion chamber 1 can communicate with the external environment of the micro-combustion chamber 1 through the outer annular cavity 12, so that the external environment of the micro-combustion chamber 1 can deliver air 17 to the outer annular cavity 12. Optionally, the micro-combustion chamber 1 is provided with a compressor impeller 50, which is located at one end of the outer annular cavity 12. When the compressor impeller 50 operates, it can draw air 17 from the external environment of the micro-combustion chamber 1 into the interior of the micro-combustion chamber 1, compress the drawn-in air 17, and deliver the compressed air 17 to the outer annular cavity 12.

[0031] Air 17 can flow in the outer annular cavity 12. The outer annular cavity 12 is connected to the inner annular cavity 14, and the air 17 in the outer annular cavity 12 can flow into the inner annular cavity 14. The inner annular cavity 14 is also connected to the inner cavity 13 of the flame tube, and the air 17 in the inner annular cavity 14 can flow into the inner cavity 13 of the flame tube. In this way, the outer annular cavity 12 is connected to the inner cavity 13 of the flame tube through the inner annular cavity 14, and the air 17 flows into the inner cavity 13 of the flame tube successively through the outer annular cavity 12 and the inner annular cavity 14, providing air supply for the combustion operation in the inner cavity 13 of the flame tube.

[0032] The inner cavity 13 of the flame tube and the fuel collection chamber 16 are arranged adjacent to each other, with the fuel collection chamber 16 located to the side of the inner cavity 13 of the flame tube. The fuel collection chamber 16 communicates with the inner cavity 13 of the flame tube. The micro-combustion chamber 1 is connected to a fuel device outside the micro-combustion chamber 1 through the fuel collection chamber 16, so that the fuel device outside the micro-combustion chamber 1 can supply fuel 18 to the fuel collection chamber 16. The fuel 18 can flow into the inner cavity 13 of the flame tube through the fuel collection chamber 16, providing fuel supply for the combustion operation in the inner cavity 13 of the flame tube.

[0033] In this embodiment, the fuel collection chamber 16 is disposed on the side of the flame tube inner cavity 13, away from the compressor impeller 50. The fuel collection chamber 16 can be disposed on the side of the flame tube inner cavity 13 along the axial direction of the micro-combustion chamber 1. Both the fuel collection chamber 16 and the flame tube inner cavity 13 are located between the inner annular cavity 14 and the outer annular cavity 12 along the radial direction of the micro-combustion chamber 1. This embodiment does not limit the specific location of the fuel collection chamber 16.

[0034] Both air 17 and fuel 18 can flow into the inner cavity 13 of the flame tube. Air 17 and fuel 18 can mix and participate in combustion in the inner cavity 13 of the flame tube, and burn in the inner cavity 13 of the flame tube to form high-temperature gas 19. High-temperature gas 19 can flow in the inner cavity 13 of the flame tube.

[0035] The inner cavity 13 of the flame tube is connected to the outer exhaust channel 11 via an inner exhaust channel 15, allowing the high-temperature combustion gas 19 to flow into the outer exhaust channel 11 through the inner exhaust channel 15. Specifically, the inner cavity 13 of the flame tube is connected to the inner exhaust channel 15, allowing the high-temperature combustion gas 19 in the inner cavity 13 to flow into the inner exhaust channel 15. The inner exhaust channel 15 is also connected to the outer exhaust channel 11, allowing the high-temperature combustion gas 19 in the inner exhaust channel 15 to flow into the outer exhaust channel 11 and be discharged outward through the outer exhaust channel 11. In this way, the high-temperature combustion gas 19 is discharged outward successively through the inner exhaust channel 15 and the outer exhaust channel 11.

[0036] The temperature of the high-temperature gas 19 is higher than that of the air 17. During the operation of the micro combustion chamber 1, the high-temperature gas 19 in the inner exhaust passage 15 can exchange heat with the air 17 in the inner annular cavity 14, the high-temperature gas 19 in the outer exhaust passage 11 can exchange heat with the air 17 in the outer annular cavity 12, and the high-temperature gas 19 in the inner cavity 13 of the flame tube can exchange heat with the air 17 in both the inner annular cavity 14 and the outer annular cavity 12.

[0037] In this way, the micro-combustion chamber 1 forms a regenerative structure through the cooperation of the inner annular cavity 14, the outer annular cavity 12, the inner exhaust channel 15, and the outer exhaust channel 11. The regenerative structure increases the flow time of air 17 in the micro-combustion chamber 1, and the regenerative structure is directly connected to the inner cavity 13 of the flame tube, so that the high-temperature gas 19 can fully exchange heat with the air 17. That is, the micro-combustion chamber 1 can use the exhaust waste heat of the high-temperature gas 19 to preheat the air 17, realize the recovery and utilization of heat, reduce energy consumption, and improve the overall thermal efficiency of the heat cycle. At the same time, the preheated air 17 enters the inner cavity 13 of the flame tube at a higher initial temperature, which can promote the rapid mixing and complete combustion of air 17 and fuel 18, improve combustion stability, and improve the performance of the micro-combustion chamber 1.

[0038] In this embodiment, the micro combustion chamber 1 is further provided with a turbine 70, which is located between the inner cavity 13 of the flame tube and the inner exhaust passage 15. The inner cavity 13 of the flame tube can deliver high-temperature combustion gas 19 to the turbine 70 and impact the turbine 70 to perform work. After performing work, the high-temperature combustion gas 19 is guided by the turbine 70 and delivered to the inner exhaust passage 15. The micro combustion chamber 1 is also provided with a shaft 60, and the compressor impeller 50 is connected to the turbine 70 through the shaft 60. The power generated by the turbine 70 can be transmitted to the compressor impeller 50 through the shaft 60 to drive the compressor impeller 50 to rotate. For example, after the turbine 70 is impacted by the high-temperature combustion gas 19 and performs work, it drives the shaft 60 to rotate. The rotation of the shaft 60 can drive the compressor impeller 50 to rotate, so that the compressor impeller 50 can continuously draw in and compress air 17 and stably deliver the compressed air 17 to the outer annular cavity 12, providing sufficient air 17 for subsequent combustion operations. In this way, the high-temperature gas in the inner cavity 13 of the flame tube can drive the turbine 70 to do work and provide power for the operation of the compressor impeller 50; it can also be guided by the turbine 70 to deliver the high-temperature gas 19 to the internal exhaust channel 15 to ensure that the compressed air and gas can operate continuously and stably during the work process.

[0039] According to this application, a micro combustion chamber 1 with a heat recovery structure is used in a gas turbine. It includes a fluid passage 10, through which air 17 and fuel 18 can flow. The fluid passage 10 is provided with an external exhaust passage 11, an outer annular cavity 12, a flame tube inner cavity 13, an inner annular cavity 14, an internal exhaust passage 15, and a fuel collection chamber 16. The outer annular cavity 12 is located between the external exhaust passage 11 and the flame tube inner cavity 13, and is spaced apart from both. The inner annular cavity 14 is located between the flame tube inner cavity 13 and the internal exhaust passage 15, and is spaced apart from both. The fuel collection chamber 16 and the flame tube inner cavity 13 are both located between the inner annular cavity 14 and the outer annular cavity 12. The outer annular cavity 12 is connected to the flame tube inner cavity 13 through the inner annular cavity 14, and air 17 flows through it sequentially. The fuel 18 flows into the inner cavity 13 of the flame tube through the outer annular cavity 12 and the inner annular cavity 14; the fuel gas collection chamber 16 is connected to the inner cavity 13 of the flame tube along the axial direction of the micro combustion chamber 1, and the fuel 18 can flow into the inner cavity 13 of the flame tube through the fuel gas collection chamber 16; the inner cavity 13 of the flame tube is connected to the outer exhaust channel 11 through the inner exhaust channel 15, and the air 17 and fuel 18 are burned in the inner cavity 13 of the flame tube to form high-temperature gas 19, and the high-temperature gas 19 flows into the outer exhaust channel 11 through the inner exhaust channel 15; wherein, the high-temperature gas 19 in the inner exhaust channel 15 can exchange heat with the air 17 in the inner annular cavity 14, the high-temperature gas 19 in the outer exhaust channel 11 can exchange heat with the air 17 in the outer annular cavity 12, and the high-temperature gas 19 in the inner cavity 13 of the flame tube can exchange heat with the air 17 in both the inner annular cavity 14 and the outer annular cavity 12. In this way, the micro combustion chamber 1, through the cooperation of the outer annular cavity 12, the inner annular cavity 14, the external exhaust channel 11, and the internal exhaust channel 15, increases the flow time of air 17 in the micro combustion chamber 1, allowing the high-temperature combustion gas 19 to fully exchange heat with the air 17, thereby preheating the air 17, realizing heat recovery and utilization, reducing energy consumption, and improving the overall thermal efficiency of the heat cycle; at the same time, the preheated air 17 enters the inner cavity 13 of the flame tube at a higher initial temperature, which can promote the rapid mixing and complete combustion of air 17 and fuel 18, improve combustion stability, and improve the performance of the micro combustion chamber 1.

[0040] The micro-combustion chamber 1 with a heat recovery structure also includes a casing assembly 20, the interior of which has a fluid passage 10. Specifically, as... Figure 1 As shown, the casing assembly 20 includes an annular cavity channel outer casing 22 and a flame tube outer casing 23 spaced apart. The annular cavity channel outer casing 22 and the flame tube outer casing 23 are arranged coaxially, and the central axis of the annular cavity channel outer casing 22 coincides with the central axis of the flame tube outer casing 23. The annular cavity channel outer casing 22 is sleeved on the outside of the flame tube outer casing 23, and the annular cavity channel outer casing 22 and the flame tube outer casing 23 are spaced apart along the radial direction of the micro combustion chamber 1.

[0041] The outer casing 22 of the annular cavity channel is located between the external exhaust channel 11 and the outer annular cavity 12, with the external exhaust channel 11 separated from the outer annular cavity 12 by the outer casing 22. The outer casing 23 of the flame tube is located between the outer annular cavity 12 and the inner cavity 13 of the flame tube, with the outer annular cavity 12 separated from the inner cavity 13 by the outer casing 23. The outer annular cavity 12 is located between the outer casing 22 of the annular cavity channel and the outer casing 23 of the flame tube.

[0042] The casing assembly 20 also includes an inner casing 25 of the annular cavity channel and an inner casing 24 of the flame tube, which are spaced apart. An outer casing 23 of the flame tube is fitted over the inner casing 24, and the inner casing 24 is fitted over the inner casing 25 of the annular cavity channel. The central axis of the inner casing 25 of the annular cavity channel and the central axis of the inner casing 24 of the flame tube coincide with the central axis of the outer casing 23 of the flame tube. The inner casing 24 of the flame tube is located between the inner cavity 13 and the inner annular cavity 14 of the flame tube, and the inner casing 25 of the annular cavity channel is located between the inner annular cavity 14 and the inner exhaust passage 15. The inner annular cavity 14 is separated from the inner exhaust passage 15 by the inner casing 25 of the annular cavity channel.

[0043] One end of the inner casing 24 of the flame tube is connected to one end of the inner casing 25 of the annular cavity channel, and the other end of the inner casing 24 of the flame tube is connected to one end of the outer casing 23 of the flame tube. The other end of the inner casing 25 of the annular cavity channel is connected to one end of the outer casing 22 of the annular cavity channel. Optionally, the inner casing 24 of the flame tube can be welded to the inner casing 25 of the annular cavity channel to achieve a certain structural strength. The inner casing 24 of the flame tube can be welded to the outer casing 23 of the flame tube to achieve a certain structural strength. The inner casing 25 of the annular cavity channel can be welded to the outer casing 22 of the annular cavity channel to achieve a certain structural strength. This application embodiment does not limit the connection method between the inner casing 24 of the flame tube and the inner casing 25 of the annular cavity channel, nor does it limit the connection method between the inner casing 24 of the flame tube and the outer casing 23 of the flame tube, nor does it limit the connection method between the inner casing 25 of the annular cavity channel and the outer casing 22 of the annular cavity channel.

[0044] One end of the outer casing 23 of the flame tube is fixedly connected to the inner casing 24 of the flame tube, and the other end of the outer casing 23 can be rotatably connected to the shaft 60. The shaft 60 is rotatable relative to the outer casing 23 of the flame tube. Optionally, the shaft 60 can be rotatably connected to the outer casing 23 of the flame tube via a bearing. The compressor impeller 50 and the turbine 70 can be located at opposite ends of the shaft 60 along the axial direction of the micro-combustion chamber 1. The embodiments of this application do not limit the connection method between the shaft 60 and the outer casing 23 of the flame tube.

[0045] In this way, through the cooperation of the outer casing 22 of the annular cavity channel, the outer casing 23 of the flame tube, the inner casing 25 of the annular cavity channel, and the inner casing 24 of the flame tube, the outer annular cavity 12 is located between the outer casing 22 of the annular cavity channel and the outer casing 23 of the flame tube, the inner cavity 13 of the flame tube is located between the outer casing 23 of the flame tube and the inner casing 24 of the flame tube, the inner annular cavity 14 is located between the inner casing 25 of the annular cavity channel and the inner casing 24 of the flame tube, and the inner exhaust channel 15 is located inside the inner casing 25 of the annular cavity channel.

[0046] The casing assembly 20 also includes an exhaust channel outer casing 21 spaced apart from the annular cavity channel outer casing 22, with the exhaust channel outer casing 21 fitted over the annular cavity channel outer casing 22. The central axis of the annular cavity channel outer casing 22 coincides with the central axis of the exhaust channel outer casing 21. The other end of the annular cavity channel outer casing 22 is connected to the exhaust channel outer casing 21, and the external exhaust channel 11 is located between the annular cavity channel outer casing 22 and the exhaust channel outer casing 21. Optionally, the annular cavity channel outer casing 22 can be welded to the exhaust channel outer casing 21 to achieve a certain structural strength. This application embodiment does not limit the connection method between the annular cavity channel outer casing 22 and the exhaust channel outer casing 21.

[0047] like Figure 2 As shown, the outer annular cavity 12, the inner cavity of the flame tube 13, the inner annular cavity 14, the inner exhaust channel 15, and the outer exhaust channel 11 together form a directional and stable fluid flow path, so that air 17 flows into the inner cavity of the flame tube 13 through the outer annular cavity 12 and the inner annular cavity 14. After the air 17 and fuel 18 are burned in the inner cavity of the flame tube 13, the high-temperature gas 19 flows into the outer exhaust channel 11 through the inner exhaust channel 15 and is discharged to the outside of the micro combustion chamber 1 through the outer exhaust channel 11.

[0048] Specifically, the high-temperature gas 19 in the external exhaust passage 11 exchanges heat with the air 17 in the outer annular cavity 12 through the outer casing 22 of the annular cavity passage, thereby preheating the air 17 in the outer annular cavity 12; the high-temperature gas 19 in the inner cavity 13 of the flame tube exchanges heat with the air 17 in the outer annular cavity 12 through the outer casing 23 of the flame tube, thereby preheating the air 17 in the outer annular cavity 12. The high-temperature gas 19 in the internal exhaust passage 15 exchanges heat with the air 17 in the inner annular cavity 14 through the inner casing 25 of the annular cavity passage, thereby preheating the air 17 in the inner annular cavity 14; the high-temperature gas 19 in the inner cavity 13 of the flame tube exchanges heat with the air 17 in the inner annular cavity 14 through the inner casing 24 of the flame tube, thereby preheating the air 17 in the inner annular cavity 14. In this way, the high-temperature gas 19 can fully exchange heat with the air 17 to fully preheat the air 17, realize the recovery and utilization of heat, reduce energy consumption, and improve the overall thermal efficiency of the heat cycle. At the same time, the preheated air 17 enters the inner cavity 13 of the flame tube at a higher initial temperature, which can promote the rapid mixing and full combustion of air 17 and fuel 18, improve combustion stability, and improve the performance of the micro combustion chamber 1.

[0049] Optionally, the exhaust channel outer casing 21, the annular cavity channel outer casing 22, the flame tube outer casing 23, the flame tube inner casing 24, and the annular cavity channel inner casing 25 can all be made of high-temperature alloy materials to adapt to the working environment of the micro combustion chamber 1. The wall thickness of the exhaust channel outer casing 21, the annular cavity channel outer casing 22, the flame tube outer casing 23, the flame tube inner casing 24, and the annular cavity channel inner casing 25 is 0.5mm-1.5mm, and the height of the outer exhaust channel 11, the outer annular cavity 12, the inner annular cavity 14, and the inner exhaust channel 15 is 1.5-2.5mm to meet the requirements of lightweight, compact, and efficient micro combustion chamber 1. By controlling the area-to-volume ratio of the micro combustion chamber 1, the heat exchange efficiency is improved and the energy loss is reduced, enabling the air 17 to fully absorb the heat of the high-temperature combustion gas 19 and achieve preheating of the air 17; it also enables the air 17 to quickly and evenly mix with the fuel 18 after entering the inner cavity 13 of the flame tube, improving combustion stability and reducing energy waste caused by incomplete combustion.

[0050] The micro-combustion chamber 1 with a heat recovery structure also includes a fuel inlet 30. One end of the fuel inlet 30 is connected to a fuel device outside the micro-combustion chamber 1, and the other end of the fuel inlet 30 is inserted into the fuel collection chamber 16. The fuel inlet 30 is used to deliver fuel 18. The fuel inlet 30 is capable of delivering fuel 18 to the fuel collection chamber 16.

[0051] In this embodiment, the fuel inlet 30 passes through the outer casing 21 of the exhaust channel and the outer casing 22 of the annular cavity channel and is then inserted into the outer casing 23 of the flame tube. The axial direction of the fuel inlet 30 can be parallel to the axial direction of the micro-combustion chamber 1. As an optional implementation, the axial direction of the fuel inlet 30 can intersect the axial direction of the micro-combustion chamber 1. For example, the fuel inlet 30 passes through the outer casing 21 of the exhaust channel and the inner casing 25 of the annular cavity channel and is then inserted into the inner casing 24 of the flame tube, so that the fuel inlet 30 can be inserted into the fuel collection chamber 16 at an angle. This embodiment does not limit the specific installation method of the fuel inlet 30, as long as it can deliver fuel 18 to the fuel collection chamber 16.

[0052] Optionally, the fuel inlet 30 can be made of a high-temperature alloy material to adapt to the working environment of the micro combustion chamber 1. The fuel inlet 30 and the casing assembly 20 can be connected together by welding to achieve a certain structural strength. This application embodiment does not limit the specific manner or location of the fuel inlet 30 penetrating the casing assembly 20, as long as the fuel inlet 30 is fixedly connected to the casing assembly 20 and inserted into the fuel collection chamber 16. In this way, fuel 18 can be stably delivered to the fuel collection chamber 16 through the fuel inlet 30, ensuring the normal operation of the micro combustion chamber 1.

[0053] The interior of fuel inlet 30 is spaced apart from the external exhaust passage 11, and also spaced apart from the outer annular cavity 12. Simultaneously, the interior of fuel inlet 30 is spaced apart from the internal exhaust passage 15, and also spaced apart from the inner annular cavity 14. Fuel inlet 30 is connected to fuel collection chamber 16, allowing fuel 18 to flow into it. Fuel 18 can flow within fuel collection chamber 16. Fuel collection chamber 16 is connected to the inner cavity 13 of the flame tube. Fuel inlet 30 can deliver fuel 18 to the inner cavity 13 of the flame tube through fuel collection chamber 16.

[0054] The micro-combustion chamber 1 with a heat recovery structure also includes an air inlet 40 and a fuel inlet 30, which are spaced apart. The air inlet 40 is used to supply air 17. The air inlet 40 protrudes from the casing assembly 20 and extends outward along the axial direction of the micro-combustion chamber 1. In the embodiments of this application, the axial direction of the air inlet 40 is parallel to the axial direction of the fuel inlet 30. The air inlet 40 and the fuel inlet 30 are located at opposite ends of the micro-combustion chamber 1 along the axial direction of the micro-combustion chamber 1. The embodiments of this application do not limit the positions of the air inlet 40 and the fuel inlet 30.

[0055] Air inlet 40 is connected to outer annular cavity 12, and air 17 can flow into outer annular cavity 12 through first air inlet 40. Outer annular cavity 12 is connected to inner annular cavity 14, and air 17 can flow into inner annular cavity 14 through outer annular cavity 12. Optionally, compressor impeller 50 can be disposed between air inlet 40 and outer annular cavity 12.

[0056] In this way, the flow path of air 17 is separated from the flow path of fuel 18, effectively preventing air 17 and fuel 18 from mixing before flowing into the inner cavity 13 of the flame tube. This allows the flow rates of air 17 and fuel 18 to be adjusted independently, thereby adjusting the mixing ratio of air 17 and fuel 18 and ensuring complete combustion. At the same time, the air 17 flows around the inner cavity 13 of the flame tube, which can preheat the air 17, improve the overall thermal efficiency of the heat cycle, promote the rapid mixing and complete combustion of air 17 and fuel 18, improve combustion stability, and improve the performance of the micro combustion chamber 1. In addition, fuel 18 flows directly into the inner cavity 13 of the flame tube through the fuel collection chamber 16, effectively preventing the fuel 18 from heating up, vaporizing, or undergoing compositional changes during transportation, ensuring the normal operation of the micro combustion chamber 1.

[0057] The inner annular cavity 14 is connected to the inner cavity 13 of the flame tube. As an optional embodiment, the inner casing 24 of the flame tube is provided with a main combustion port 241, which penetrates the inner casing 24 and whose axial direction is perpendicular to the axial direction of the micro-combustion chamber 1. The main combustion port 241 penetrates the inner casing 24 of the flame tube along its axial direction. The inner annular cavity 14 is connected to the inner cavity 13 of the flame tube through the main combustion port 241, allowing air 17 in the inner annular cavity 14 to flow into the inner cavity 13 of the flame tube through the main combustion port 241. Optionally, the diameter of the main combustion port 241 can be 1.4 mm. The main combustion port 241 can be a vertical hole, an oblique hole, or a tangential hole; the specific structure of the main combustion port 241 is not limited in this embodiment.

[0058] In this way, by adjusting the diameter of the main combustion orifice 241, the flow rate of air 17 injected into the inner cavity 13 of the flame tube can be precisely adjusted, ensuring that the combustion zone in the inner cavity 13 of the flame tube can be maintained within the range of high-efficiency combustion. At the same time, the preheated air 17 in the inner ring cavity 14 is injected into the inner cavity 13 of the flame tube in the form of a jet through the main combustion orifice 241, which can promote the mixing of air 17 and fuel 18 in the inner cavity 13 of the flame tube, shorten the mixing time, and improve the combustion reaction rate. In addition, the jet from the main combustion orifice 241 can also form a recirculation zone at the head of the flame tube, effectively improving flame stability and enhancing the operational reliability and combustion efficiency of the micro combustion chamber 1.

[0059] The inner casing 24 of the flame tube is provided with at least two main combustion holes 241, which are spaced apart along the circumferential direction of the inner casing 24. The circumferential direction of the inner casing 24 is perpendicular to the axial direction of the micro-combustion chamber 1. Preferably, the main combustion holes 241 have the same structure. The at least two main combustion holes 241 are equidistantly arranged along the circumferential direction of the inner casing 24. Similarly, the inner casing 24 may be provided with more main combustion holes 241, and this application does not limit the number of main combustion holes 241.

[0060] In this way, the multiple main combustion holes 241 can uniformly inject the preheated air 17 in the inner annular cavity 14 into the inner cavity 13 of the flame tube in the form of multiple jets, so that the preheated air 17 can be evenly distributed along the circumferential direction of the inner cavity 13 of the flame tube, ensuring that the air 17 and the fuel 18 can be evenly mixed, effectively improving the combustion reaction rate and combustion efficiency; in addition, the multiple jets can form a stable circumferential backflow zone at the head of the flame tube, further improving the flame stability and enhancing the mixing effect of air 17 and fuel 18, thus expanding the stable operating range of the micro combustion chamber 1.

[0061] As an alternative implementation, the inner casing 24 of the flame tube is provided with a main combustion port 241 and a mixing port 242 spaced apart along the axial direction of the micro-combustion chamber 1. Both the main combustion port 241 and the mixing port 242 penetrate the inner casing 24 of the flame tube, and the inner annular cavity 14 communicates with the inner cavity 13 of the flame tube through the main combustion port 241 and the mixing port 242. The main combustion port 241 is closer to the fuel collection chamber 16 than the mixing port 242. The main combustion port 241 is used to output air 17 for combustion into the inner cavity 13 of the flame tube. The mixing port 242 is used to adjust the mixing ratio of air 17 and fuel 18 in the inner cavity 13 of the flame tube. The air 17 in the inner annular cavity 14 can flow into the inner cavity 13 of the flame tube through the main combustion port 241 and the mixing port 242. Optionally, the diameter of the main combustion hole 241 can be 1.4 mm, and the diameter of the mixing hole 242 can be 1.2 mm, so that the air 17 in the inner annular cavity 14 can be injected into the inner cavity 13 of the flame tube in a jet manner. Both the main combustion hole 241 and the mixing hole 242 can be vertical holes, oblique holes, and tangential holes. The specific structure of the main combustion hole 241 and the mixing hole 242 is not limited in the embodiments of this application.

[0062] In this way, the preheated air 17 in the inner ring cavity 14 is divided into two jets through the main combustion port 241 and the mixing port 242 and flows into the inner cavity 13 of the flame tube. The air 17 ejected from the main combustion port 241 directly participates in combustion, while the air 17 ejected from the mixing port 242 is distributed to maintain the air 17 and fuel 18 in the combustion zone at a near-chemically appropriate ratio, which effectively improves the combustion efficiency and broadens the stable operating range of the micro combustion chamber 1. Furthermore, the backflow zone generated by the jet from the main combustion port 241 at the head of the flame tube can play a dual role in stabilizing the flame and enhancing the mixing of air 17 and fuel 18, further optimizing the combustion effect.

[0063] The inner casing 24 of the flame tube is provided with at least two main combustion holes 241 and at least two mixing holes 242. The at least two main combustion holes 241 are spaced apart along the circumferential direction of the inner casing 24, and the at least two mixing holes 242 are also spaced apart along the circumferential direction of the inner casing 24. The circumferential direction of the inner casing 24 is perpendicular to the axial direction of the micro-combustion chamber 1. Preferably, the main combustion holes 241 and the mixing holes 242 are identical in construction. The at least two main combustion holes 241 and the at least two mixing holes 242 are equidistantly arranged along the circumferential direction of the inner casing 24. In the embodiments of this application, the inner casing 24 of the flame tube is provided with 12 main combustion holes 241 and 12 mixing holes 242. This application does not limit the specific number of main combustion holes 241 and mixing holes 242.

[0064] In this way, multiple main combustion holes 241 and multiple mixing holes 242 can uniformly inject the preheated air 17 in the inner annular cavity 14 into the inner cavity 13 of the flame tube in the form of multiple jets. This allows the preheated air 17 to be evenly distributed along the circumferential direction of the inner cavity 13 of the flame tube, ensuring that the air 17 and fuel 18 in the inner cavity 13 of the flame tube can be fully and evenly mixed together, further improving the uniformity and stability of combustion, thereby improving the overall combustion efficiency of the micro combustion chamber 1. At the same time, multiple mixing holes 242 can replenish the air 17 in the inner cavity 13 of the flame tube along the circumferential direction of the inner cavity 13 of the flame tube, so that the air 17 and fuel 18 in the combustion zone are maintained at a near-chemically appropriate ratio for combustion, further improving combustion efficiency and expanding the stable operating range of the micro combustion chamber 1. In addition, multiple jets can form a stable and uniform circumferential recirculation zone at the head of the flame tube, further improving flame stability.

[0065] The casing assembly 20 also includes a first connecting member 26, which is located radially between the outer casing 23 and the inner casing 24 of the flame tube, with its central axis coinciding with the central axis of the inner casing 24. The two ends of the first connecting member 26 are connected to the outer casing 23 and the inner casing 24, respectively. The first connecting member 26 is located axially between the inner cavity 13 and the fuel collection chamber 16 of the flame tube. The inner cavity 13 is separated from the fuel collection chamber 16 by the first connecting member 26.

[0066] Optionally, the first connecting member 26 can be made of a high-temperature alloy material to adapt to the working environment of the micro combustion chamber 1. The wall thickness of the first connecting member 26 can be 0.5mm-1.5mm to meet the requirements of lightweight, compact, and efficient micro combustion chamber 1. The first connecting member 26 can be connected to the outer casing 23 of the flame tube by welding, and the first connecting member 26 can be connected to the inner casing 24 of the flame tube by welding. This application embodiment does not limit the connection method between the first connecting member 26 and the outer casing 23 of the flame tube, nor does it limit the connection method between the first connecting member 26 and the inner casing 24 of the flame tube.

[0067] The inner cavity 13 of the flame tube is connected to the fuel collection chamber 16. A first connecting member 26 is provided with an injection hole 261, which penetrates the first connecting member 26 along its axial direction. The axial direction of the injection hole 261 is parallel to the axial direction of the micro-combustion chamber 1. The fuel collection chamber 16 is connected to the inner cavity 13 of the flame tube through the injection hole 261, and fuel 18 in the fuel collection chamber 16 flows into the inner cavity 13 of the flame tube through the injection hole 261. Optionally, the diameter of the injection hole 261 can be 0.4 mm, so that fuel 18 can be injected into the inner cavity 13 of the flame tube through the injection hole 261 in the fuel collection chamber 16 and mix with air 17 to participate in combustion. The injection hole 261 can be a vertical hole, an oblique hole, or a tangential hole; the specific structure of the injection hole 261 is not limited in this embodiment.

[0068] The first connecting member 26 is provided with at least two injection holes 261, which are spaced apart along the circumferential direction of the first connecting member 26. The circumferential direction of the first connecting member 26 is perpendicular to the axial direction of the micro combustion chamber 1. Preferably, the injection holes 261 have the same structure as each other. The at least two injection holes 261 are equidistantly arranged along the circumferential direction of the first connecting member 26. In the embodiments of this application, the inner casing 24 of the flame tube is provided with 12 injection holes 261. This application does not limit the specific number of injection holes 261.

[0069] At least two main combustion holes 241 correspond one-to-one with at least two injection holes 261. In this embodiment, the inner casing 24 of the flame tube is provided with 12 main combustion holes 241, and the first connecting member 26 is provided with 12 injection holes, with each of the 12 main combustion holes 241 corresponding one-to-one with the 12 injection holes 261. This application does not limit the specific number of main combustion holes 241 and injection holes 261.

[0070] The main combustion port 241 and the injection port 261 are arranged opposite each other along the axial direction of the micro-combustion chamber 1. In this way, the air 17 in the inner annular cavity 14 can flow into the inner cavity 13 of the flame tube through the main combustion port 241, and the fuel 18 in the fuel collection chamber 16 can flow into the inner cavity 13 of the flame tube through the injection port 261. The two fluids form opposing jets in the inner cavity 13 of the flame tube, which enhances the mixing effect between the air 17 and the fuel 18, shortens the mixing time, and enables the air 17 and the fuel 18 to be mixed uniformly. At the same time, the correspondence between the main combustion port 241 and the injection port 261 improves the uniformity and stability of combustion, thereby improving the overall combustion efficiency of the micro-combustion chamber 1 and enhancing the operational stability of the micro-combustion chamber 1.

[0071] The outer casing 21 of the exhaust channel also includes an exhaust port 211, which penetrates the outer casing 21, allowing the high-temperature combustion gas 19 to be discharged. Optionally, the exhaust port 211 can be connected to a waste heat recovery device outside the micro combustion chamber 1 to further treat the high-temperature combustion gas 19 discharged from the micro combustion chamber 1. In this way, the high-temperature combustion gas 19 can be discharged from the micro combustion chamber 1 through the exhaust port 211 after heat exchange, reducing the temperature of the high-temperature combustion gas 19 at discharge, reducing the thermal shock of the high-temperature combustion gas 19 to the micro combustion chamber 1, and extending the service life of the micro combustion chamber 1. At the same time, the discharge of the high-temperature combustion gas 19 from the micro combustion chamber 1 also ensures the stability of the internal pressure of the micro combustion chamber 1, effectively avoiding the problems of gas accumulation and abnormal pressure rise inside the micro combustion chamber 1.

[0072] When the micro combustion chamber 1 is running, air 17 flows into the outer annular cavity 12 through the air inlet 40, and the air 17 in the outer annular cavity 12 flows into the inner cavity 13 of the flame tube through the main combustion hole 241 of the inner annular cavity 14; fuel 18 flows into the fuel collection chamber 16 through the fuel inlet 30, and the fuel 18 in the fuel collection chamber 16 is injected into the inner cavity 13 of the flame tube through the injection hole 261 of the first connecting member 26; the air 17 and fuel 18 in the inner cavity 13 of the flame tube participate in combustion to form high-temperature gas 19, and the high-temperature gas 19 can flow into the outer exhaust passage 11 through the inner exhaust passage 15 and be discharged through the exhaust port 211.

[0073] During the flow of air 17 through the outer annular cavity 12 and the inner annular cavity 14, it is heated by the high-temperature combustion gas 19, which carries away some of the heat from the high-temperature combustion gas 19 in the outer exhaust passage 11, the inner exhaust passage 15, and the inner cavity of the flame tube 13, thereby reducing the exhaust temperature, realizing heat recovery and utilization, reducing energy consumption, and improving the overall thermal efficiency of the heat cycle. At the same time, the preheated air 17 enters the inner cavity of the flame tube 13 at a higher initial temperature, which can promote the rapid mixing and complete combustion of air 17 and fuel 18, improve combustion stability, and improve combustion chamber performance.

[0074] Furthermore, the preheated air 17 enters the inner cavity 13 of the flame tube through the main combustion port 241 and mixing port 242 provided in the inner casing 24 of the flame tube to participate in combustion. The splitting of the air 17 allows the air 17 and fuel 18 to be mixed evenly, and the air 17 and fuel 18 in the combustion zone of the inner cavity 13 of the flame tube can be maintained at a near chemical ratio, which effectively improves the combustion efficiency and broadens the stable working range of the micro combustion chamber 1. At the same time, the backflow zone generated by the jet of the main combustion port 241 at the head of the flame tube can play a dual role in stabilizing the flame and enhancing the mixing of air 17 and fuel 18, further optimizing the combustion effect.

[0075] This application discloses a micro combustion chamber 1 with a heat recovery structure for a gas turbine, comprising a fluid channel 10, through which air 17 and fuel 18 can flow. The fluid channel 10 is provided with an external exhaust channel 11, an outer annular cavity 12, a flame tube inner cavity 13, an inner annular cavity 14, an internal exhaust channel 15, and a fuel collection chamber 16. The outer annular cavity 12 is located between the external exhaust channel 11 and the flame tube inner cavity 13, and is spaced apart from both the external exhaust channel 11 and the flame tube inner cavity 13. The inner annular cavity 14 is located between the flame tube inner cavity 13 and the internal exhaust channel 15, and is spaced apart from the internal exhaust channel 15. The fuel collection chamber 16 and the flame tube inner cavity 13 are both located between the inner annular cavity 14 and the outer annular cavity 12. The outer annular cavity 12 is connected to the flame tube inner cavity 13 through the inner annular cavity 14, and air 17 flows through it sequentially. The fuel 18 flows into the inner cavity 13 of the flame tube through the outer annular cavity 12 and the inner annular cavity 14; the fuel gas collection chamber 16 is connected to the inner cavity 13 of the flame tube along the axial direction of the micro combustion chamber 1, and the fuel 18 can flow into the inner cavity 13 of the flame tube through the fuel gas collection chamber 16; the inner cavity 13 of the flame tube is connected to the outer exhaust channel 11 through the inner exhaust channel 15, and the air 17 and fuel 18 are burned in the inner cavity 13 of the flame tube to form high-temperature gas 19, and the high-temperature gas 19 flows into the outer exhaust channel 11 through the inner exhaust channel 15; wherein, the high-temperature gas 19 in the inner exhaust channel 15 can exchange heat with the air 17 in the inner annular cavity 14, the high-temperature gas 19 in the outer exhaust channel 11 can exchange heat with the air 17 in the outer annular cavity 12, and the high-temperature gas 19 in the inner cavity 13 of the flame tube can exchange heat with the air 17 in both the inner annular cavity 14 and the outer annular cavity 12. In this way, the micro combustion chamber 1, through the cooperation of the outer annular cavity 12, the inner annular cavity 14, the external exhaust channel 11, and the internal exhaust channel 15, increases the flow time of air 17 in the micro combustion chamber 1, allowing the high-temperature combustion gas 19 to fully exchange heat with the air 17, thereby preheating the air 17, realizing heat recovery and utilization, reducing energy consumption, and improving the overall thermal efficiency of the heat cycle; at the same time, the preheated air 17 enters the inner cavity 13 of the flame tube at a higher initial temperature, which can promote the rapid mixing and complete combustion of air 17 and fuel 18, improve combustion stability, and improve the performance of the micro combustion chamber 1.

[0076] Unless otherwise defined, the technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for descriptive purposes only and is not intended to limit the scope of this application. Terms such as “part” or “component” appearing herein can refer to a single part or a combination of multiple parts. Terms such as “installation” or “installation” appearing herein can refer to one component being directly attached to another component or one component being attached to another component via an intermediary. A feature described in one embodiment herein may be applied, alone or in combination with other features, to another embodiment, unless that feature is not applicable in that other embodiment or is otherwise stated.

[0077] This application has been described through the above embodiments; however, it should be understood that the above embodiments are for illustrative purposes only and are not intended to limit this application to the described embodiments. Furthermore, those skilled in the art will understand that this application is not limited to the above embodiments, and many more variations and modifications can be made based on the teachings of this application, all of which fall within the scope of protection claimed in this application. The scope of protection of this application is defined by the appended claims and their equivalents.

Claims

1. A miniature combustion chamber (1) with a heat recovery structure for a gas turbine, characterized in that, include: A fluid channel (10) is provided, through which air (17) and fuel (18) can circulate. The fluid channel (10) is provided with an external exhaust channel (11), an outer annular cavity (12), a flame tube inner cavity (13), an inner annular cavity (14), an internal exhaust channel (15), and a fuel gas collection chamber (16). The outer annular cavity (12) is located between the external exhaust channel (11) and the flame tube inner cavity (13), and the outer annular cavity (12) is spaced apart from both the external exhaust channel (11) and the flame tube inner cavity (13). The inner annular cavity (14) is located between the flame tube inner cavity (13) and the internal exhaust channel (15), and the inner annular cavity (14) is spaced apart from the internal exhaust channel (15). The fuel gas collection chamber (16) and the flame tube inner cavity (13) are both located between the inner annular cavity (14) and the outer annular cavity (12). The outer annular cavity (12) is connected to the inner cavity of the flame tube (13) through the inner annular cavity (14). The air (17) flows into the inner cavity of the flame tube (13) through the outer annular cavity (12) and the inner annular cavity (14) respectively. The fuel gas collection cavity (16) is connected to the inner cavity of the flame tube (13). The fuel (18) can flow into the inner cavity of the flame tube (13) through the fuel gas collection cavity (16). The inner cavity of the flame tube (13) is connected to the outer exhaust channel (11) through the inner exhaust channel (15). The air (17) and the fuel (18) are burned in the inner cavity of the flame tube (13) to form high-temperature gas (19). The high-temperature gas (19) flows into the outer exhaust channel (11) through the inner exhaust channel (15). The high-temperature gas (19) in the inner exhaust channel (15) can exchange heat with the air (17) in the inner annular cavity (14), the high-temperature gas (19) in the outer exhaust channel (11) can exchange heat with the air (17) in the outer annular cavity (12), and the high-temperature gas (19) in the inner cavity (13) of the flame tube can exchange heat with the air (17) in the inner annular cavity (14) and the outer annular cavity (12).

2. The micro combustion chamber (1) with a heat recovery structure according to claim 1, characterized in that, The micro combustion chamber (1) with a heat recovery structure also includes a casing assembly (20), which includes an annular cavity channel outer casing (22) and a flame tube outer casing (23) spaced apart. The annular cavity channel outer casing (22) is sleeved on the outside of the flame tube outer casing (23), and the outer annular cavity (12) is located between the annular cavity channel outer casing (22) and the flame tube outer casing (23).

3. The micro combustion chamber (1) with a heat recovery structure according to claim 2, characterized in that, The casing assembly (20) further includes an annular cavity channel inner casing (25) and a flame tube inner casing (24) spaced apart. The flame tube inner casing (24) is sleeved on the outside of the annular cavity channel inner casing (25). One end of the flame tube inner casing (24) is connected to one end of the annular cavity channel inner casing (25), and the other end of the flame tube inner casing (24) is connected to one end of the flame tube outer casing (23). The other end of the annular cavity channel inner casing (25) is connected to one end of the annular cavity channel outer casing (22). The inner cavity (13) of the flame tube is located between the outer casing (23) of the flame tube and the inner casing (24) of the flame tube. The inner annular cavity (14) is located between the inner casing (25) of the annular cavity channel and the inner casing (24) of the flame tube. The inner exhaust channel (15) is located inside the inner casing (25) of the annular cavity channel.

4. The micro combustion chamber (1) with a heat recovery structure according to claim 3, characterized in that, The casing assembly (20) further includes an exhaust channel outer casing (21) spaced apart from the annular cavity channel outer casing (22). The exhaust channel outer casing (21) is sleeved on the outside of the annular cavity channel outer casing (22). The other end of the annular cavity channel outer casing (22) is connected to the exhaust channel outer casing (21). The external exhaust channel (11) is located between the annular cavity channel outer casing (22) and the exhaust channel outer casing (21).

5. The micro combustion chamber (1) with a heat recovery structure according to claim 4, characterized in that, The micro combustion chamber (1) with a heat recovery structure also includes a fuel inlet (30), which passes through the exhaust channel outer casing (21) and the annular cavity channel outer casing (22) and is inserted into the flame tube outer casing (23). The fuel inlet (30) is connected to the fuel collection chamber (16), and the fuel (18) can flow into the fuel collection chamber (16) through the fuel inlet (30).

6. The micro combustion chamber (1) with a heat recovery structure according to claim 5, characterized in that, The micro combustion chamber (1) with a heat recovery structure also includes an air inlet (40) and a fuel inlet (30). The air inlet (40) and the fuel inlet (30) are located at both ends of the micro combustion chamber (1) along the axial direction of the micro combustion chamber (1). The air inlet (40) is used to transport the air (17). The air inlet (40) is connected to the outer annular cavity (12). The air (17) can flow into the outer annular cavity (12) through the air inlet (40).

7. The micro combustion chamber (1) with a heat recovery structure according to claim 3, characterized in that, The inner casing (24) of the flame tube is provided with a main combustion port (241), which penetrates the inner casing (24) of the flame tube, and the inner annular cavity (14) is connected to the inner cavity (13) of the flame tube through the main combustion port (241); Alternatively, the inner casing (24) of the flame tube is provided with a main combustion port (241) and a mixing port (242) spaced apart. Both the main combustion port (241) and the mixing port (242) penetrate the inner casing (24) of the flame tube, and the inner annular cavity (14) is connected to the inner cavity (13) of the flame tube through the main combustion port (241) and the mixing port (242).

8. The micro combustion chamber (1) with a heat recovery structure according to claim 3, characterized in that, The casing assembly (20) further includes a first connecting member (26), the two ends of which are connected to the outer casing (23) of the flame tube and the inner casing (24) of the flame tube, respectively. The first connecting member (26) is located between the inner cavity (13) of the flame tube and the fuel gas collection chamber (16) along the axial direction of the micro combustion chamber (1).

9. The micro combustion chamber (1) with a heat recovery structure according to claim 8, characterized in that, The first connecting member (26) is provided with an injection hole (261). The fuel gas collection chamber (16) is connected to the inner cavity of the flame tube (13) through the injection hole (261). The fuel (18) in the fuel gas collection chamber (16) flows into the inner cavity of the flame tube (13) through the injection hole (261). The inner casing (24) of the flame tube is provided with a main combustion port (241), and the main combustion port (241) and the injection port (261) are arranged opposite each other along the axial direction of the micro combustion chamber (1).

10. The micro combustion chamber (1) with a heat recovery structure according to claim 4, characterized in that, The exhaust channel outer casing (21) also includes an exhaust port (211), which penetrates the exhaust channel outer casing (21), and the high-temperature gas (19) can be discharged through the exhaust port (211).

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