Integrated small turbojet engine combustion chamber

Abstract

The utility model discloses an integrated small turbojet engine combustion chamber, and belongs to the technical field of turbojet engine flame tubes. Comprising an outer flame tube and an inner flame tube fixedly connected with the outer flame tube through a head plate, and an annular fuel oil atomization evaporation tube is arranged between the inner flame tube and the outer flame tube and fixedly connected with the outer flame tube; the annular fuel oil atomization evaporation pipe comprises a wheel disc connected with the outer flame tube, a plurality of curved spray pipes are evenly arranged on one side of the wheel disc, and two oil inlet nozzles are symmetrically arranged on the other side of the wheel disc. The projection of a nozzle of each curved spray pipe on the wheel disc coincides with an inlet of the second curved spray pipe rotating anticlockwise, and the nozzles are designed to be flat. According to the integrated small-sized turbojet engine combustion chamber adopting the structure, the combustion reliability and the combustion efficiency are improved, a good rectification effect on vortex is achieved, meanwhile, an oil needle is directly omitted, disassembly is easier, and the blockage problem is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of turbojet engine flame tubes, in particular to an integrated small turbojet engine combustion chamber. Background Art

[0002] A turbojet engine generally refers to a turbojet engine, which is a device that completely relies on the flow of gas to generate thrust to drive other objects. It is often used as a power source for high-speed aircraft. The structure of a turbojet engine consists of an air inlet, a compressor, a combustion chamber, a turbine and a tail nozzle. Among them, air enters the engine through the air inlet, and the air is pressurized by the compressor and diffuser. The pressurized air enters the combustion chamber and is heated by the combustion chamber. The high-temperature and high-pressure gas flowing out of the combustion chamber flows through the turbine and is finally ejected from the tail nozzle. The smooth ignition during the engine start-up process is an important indicator of the overall performance of the engine. To achieve ignition of an aircraft engine, the atomized fuel in the combustion chamber needs to be ignited by a hot plug. After ignition, as a steady stream of compressed air enters the combustion chamber, coupled with the subsequent continuous replenishment of fuel, the engine can achieve continuous work.

[0003] The combustion chamber is the core component of a micro-turbojet engine, which is equivalent to the heart of the engine. It is located between the compressor and the turbine, and is responsible for igniting the fuel and compressed air to generate high-temperature combustion gas to provide energy for the turbine. However, the combustion chamber of a micro-turbojet engine currently has problems such as insufficient combustion, the combustion speed of the fuel is much lower than the expansion speed of the combustion gas, insufficient amount of combustion gas that can be effectively utilized, and more fuel required. At the same time, higher requirements are placed on the design of the mixing hole and the main combustion hole. The combustion intake channel under a certain combustion standard must be designed according to the specified flow rate of the fuel. In addition, the flame tube structure of the micro-turbojet engine is currently complex, with many parts, and the oil needle is easily clogged and damaged. The intake redundancy of the main combustion hole and the mixing hole is low. In response to the above problems, the utility model proposes an integrated small turbojet engine combustion chamber. Utility Model Content

[0004] The utility model aims to provide an integrated small turbojet engine combustion chamber to solve the problems raised in the above-mentioned background technology and improve the combustion efficiency.

[0005] To achieve the above-mentioned purpose, the utility model provides an integrated small turbojet engine combustion chamber, comprising an outer flame tube and an inner flame tube fixedly connected to the outer flame tube through a head plate, an annular fuel atomizing evaporation pipe is arranged between the inner flame tube and the outer flame tube, and the annular fuel atomizing evaporation pipe is fixedly connected to the outer flame tube;

[0006] The annular fuel atomizing evaporation tube comprises a wheel disk connected to the outer flame tube, a plurality of curved nozzles are evenly arranged on one side of the wheel disk, and two fuel inlet nozzles are symmetrically arranged on the other side of the wheel disk.

[0007] Preferably, the projection of the nozzle of each curved nozzle on the wheel coincides with the inlet of the second curved nozzle rotated counterclockwise, and the nozzle is designed as a flat nozzle.

[0008] Preferably, a plurality of inner main combustion holes and inner mixing holes are provided on the inner flame tube, and the area of ​​the inner main combustion hole is 4 times that of the inner mixing hole.

[0009] Preferably, starting from the side close to the head plate, the internal mixing holes are evenly opened in 5 annular arrays, and the number of holes in each array is 24, 14, 12, 14, and 12; the internal main combustion holes are alternately opened in 2 circles of 12 holes at the tail of the inner flame tube.

[0010] Preferably, a plurality of outer main combustion holes and outer mixing holes are provided on the outer flame tube, and the area of ​​the outer main combustion holes is 8 times that of the outer mixing holes.

[0011] Preferably, starting from the side close to the head plate, the external mixing holes are evenly opened in 5 annular arrays, and the number of holes in each array is 48, 24, 24, 24, and 24; the external main combustion holes are alternately opened in a circle of 24 holes at the tail of the outer flame tube.

[0012] Preferably, 12 rectangular holes are evenly formed on the head plate.

[0013] Therefore, compared with the prior art, the integrated small turbojet engine combustion chamber of the utility model has the following specific beneficial effects:

[0014] (1) The annular fuel atomizing evaporator tube of the utility model adopts the curved tube evaporator tube technology, which has the advantages of good combustion reliability and high combustion efficiency;

[0015] (2) The annular fuel atomizing evaporation tube of the utility model has a good rectifying effect on the vortex;

[0016] (3) The curved tube evaporator of the annular fuel atomization evaporator omits the oil needle compared to the traditional straight injection tube, making it easier to disassemble and maintain, and avoiding blockage problems;

[0017] (4) The curved nozzle adopts a flat-mouth atomization design, and the atomization effect is better than that of oil needle atomization;

[0018] (5) The overall evaporation tube adopts an integrated design, which reduces the number of parts and improves the reliability of parts.

[0019] The technical solution of the utility model is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the overall structure of an integrated small turbojet engine combustion chamber of the utility model;

[0021] Figure 2 This is a schematic diagram of the three-dimensional structure of an annular fuel atomizing evaporation pipe of an integrated small turbojet engine combustion chamber of the utility model;

[0022] Figure 3 This is a schematic diagram of the front projection structure of an annular fuel atomizing evaporation pipe of an integrated small turbojet engine combustion chamber of the utility model;

[0023] Figure 4 This is a schematic diagram of the structure of an inner flame tube of an integrated small turbojet engine combustion chamber of the utility model;

[0024] Figure 5 This is a schematic diagram of the outer flame tube structure of an integrated small turbojet engine combustion chamber of the utility model;

[0025] Figure 6 This is a schematic diagram of the structure of a head plate of an integrated small turbojet engine combustion chamber of the utility model;

[0026] Reference numerals

[0027] 1- inner flame tube; 11- inner main combustion hole; 12- inner mixing hole;

[0028] 2-external flame tube; 21-external main combustion hole; 22-external mixing hole;

[0029] 3-Head plate;

[0030] 4-annular fuel atomizing evaporation pipe; 41-nozzle; 42-fuel inlet nozzle; 43-wheel disc. DETAILED DESCRIPTION

[0031] The technical solution of the utility model is further described below through the accompanying drawings and embodiments.

[0032] Unless otherwise defined, the words such as setting, installing, connecting, etc. in the present invention should be understood in a broad sense, and the technical personnel in the relevant technical field can reasonably determine the specific meaning of the above words in the present invention in combination with the specific content of the technical solution. The "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "include" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0033] Example

[0034] like Figure 1-6 As shown, the utility model discloses an integrated small turbojet engine combustion chamber, which includes an inner flame tube 1, an outer flame tube 2, a head plate 3, and an annular fuel atomizing evaporating tube 4. The inner flame tube 1 and the outer flame tube 2 are fixedly connected as a whole by bolts on the head plate 3, and 12 rectangular holes are evenly opened on the head plate 3; the annular fuel atomizing evaporating tube 4 is arranged between the inner flame tube 1 and the outer flame tube 2, and the annular fuel atomizing evaporating tube 4 is welded and fixed on the outer flame tube 2.

[0035] The inner flame tube 1 is provided with a plurality of inner main combustion holes 11 and inner mixing holes 12. In the present embodiment, starting from the side close to the head plate 3, the inner mixing holes are evenly arranged in five annular arrays, and the number of holes in each array is 24, 14, 12, 14, 12; the inner main combustion holes are alternately arranged in two circles of 12 holes at the tail of the inner flame tube, and the area of ​​the inner main combustion holes is four times that of the inner mixing holes.

[0036] A number of outer main combustion holes 21 and outer mixing holes 22 are provided on the outer flame tube 2. In the present embodiment, starting from the side close to the head plate 3, the outer mixing holes are evenly arranged in 5 annular arrays, and the number of holes in each array is 48, 24, 24, 24, 24; the outer main combustion holes are alternately arranged in a circle of 24 holes at the tail of the outer flame tube, and the area of ​​the outer main combustion holes is 8 times that of the external mixing holes.

[0037] The annular fuel atomizing evaporating tube 4 adopts a curved tube design, including a wheel disc 43 connected to the outer flame tube 2. A plurality of curved nozzles 41 are evenly arranged on one side of the wheel disc 43, and their nozzles adopt a flat-mouth atomization design. The projection of the nozzle of each curved nozzle 41 on the wheel disc 43 coincides with the inlet of the second curved nozzle 41 rotated counterclockwise. Two fuel inlet nozzles 42 are symmetrically arranged on the other side of the wheel disc 43.

[0038] The utility model adopts an integrated small turbojet engine combustion chamber of the above structure, which reduces the number of parts and improves the reliability of the combustion chamber. The air enters the flame tube and is atomized by the fuel nozzle. The sprayed granular fuel is evenly mixed according to the ratio. The chemical energy in the fuel is converted into thermal energy through the combustion chemical reaction to form high-temperature combustion gas, which drives the turbine to do work. The curved tube design allows the fuel to stay in the high-temperature area for a longer time, and then be atomized and sprayed from the front nozzle, thereby increasing the pressure and temperature sprayed from the nozzle, making the combustion more complete. The curved tube evaporator of the annular fuel atomization evaporator omits the oil needle compared to the traditional straight nozzle, and adopts an integrated structural design, which is easier to disassemble and more convenient to maintain, avoiding the problem of blockage.

[0039] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in this field should understand that they can still modify or replace the technical solution of the utility model with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the utility model.

Claims

1. An integrated small turbojet engine combustion chamber, characterized in that: It comprises an outer flame tube and an inner flame tube fixedly connected to the outer flame tube via a head plate, an annular fuel atomizing evaporating pipe is arranged between the inner flame tube and the outer flame tube, and the annular fuel atomizing evaporating pipe is fixedly connected to the outer flame tube; The annular fuel atomizing evaporation tube comprises a wheel disk connected to the outer flame tube, a plurality of curved nozzles are evenly arranged on one side of the wheel disk, and two fuel inlet nozzles are symmetrically arranged on the other side of the wheel disk.

2. The integrated small turbojet engine combustion chamber according to claim 1, characterized in that: The projection of the nozzle of the curved nozzle on the wheel coincides with the inlet of the second curved nozzle rotated counterclockwise, and the nozzle is designed as a flat nozzle.

3. The integrated small turbojet engine combustion chamber according to claim 1, characterized in that: The inner flame tube is provided with a plurality of inner main combustion holes and inner mixing holes, and the area of ​​the inner main combustion hole is 4 times that of the inner mixing hole.

4. The integrated small turbojet engine combustion chamber according to claim 3, characterized in that: Starting from the side close to the head plate, the internal mixing holes are evenly opened in 5 circular arrays, and the number of holes in each array is 24, 14, 12, 14, and 12; the internal main combustion holes are alternately opened in 2 circles of 12 holes at the tail of the inner flame tube.

5. The integrated small turbojet engine combustion chamber according to claim 1, characterized in that: The outer flame tube is provided with a plurality of outer main combustion holes and outer mixing holes, and the area of ​​the outer main combustion holes is 8 times that of the outer mixing holes.

6. The integrated small turbojet engine combustion chamber according to claim 5, characterized in that: Starting from the side close to the head plate, the external mixing holes are evenly opened in 5 circular arrays, and the number of holes in each array is 48, 24, 24, 24, and 24; the external main combustion holes are alternately opened in a circle of 24 holes at the tail of the outer flame tube.

7. The integrated small turbojet engine combustion chamber according to claim 1, characterized in that: The head plate is evenly provided with 12 rectangular holes.

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