Aeroengine combustion chamber testing machine cooling section spraying device

Abstract

The utility model discloses a spraying device for a cooling section of an aero-engine combustion chamber testing machine. The spraying device comprises a front flange, a rear flange, a large nozzle water spraying ring unit and a small nozzle water spraying ring unit, the large nozzle water spraying ring unit, the small nozzle water spraying ring unit, the front flange and the rear flange are connected with one another through bolts and then are mounted on the combustion chamber testing machine for detachable integrated mounting; inlets of the large nozzle water spraying ring unit and the small nozzle water spraying ring unit are mutually independent and are used for selecting a cooling scheme according to cooling requirements; the small nozzle water spraying ring unit is located close to an outlet of the combustion chamber and used for achieving the maximum heat exchange function. 10 nozzles are arranged in the large nozzle water spraying ring unit and the small nozzle water spraying ring unit at equal intervals, and the spray cone angle is 30-45 degrees, so that the contact area of spray and hot air is increased while the widest spray coverage area is achieved. According to the invention, the temperature of the tail flow of the combustion chamber tester is effectively reduced, so that test equipment and environment are protected.

Description

TECHNICAL FIELD

[0001] The utility model relates to aero -engine combustion chamber test machine cooling field especially relates to a aero -engine combustion chamber test machine cooling section spray device. BACKGROUND

[0002] One of the core components of an aero -engine is the combustion chamber, which is responsible for mixing the air sucked in and compressed by the compressor with atomized fuel and burning under high temperature conditions to produce a high-speed gas flow. This process not only is the power source for propelling the aircraft forward, but also is a key factor in determining the efficiency, reliability and environmental impact of the engine. In the aero -engine, the working temperature inside the combustion chamber can exceed 2000 DEG C, which puts high requirements on its structural materials and design.

[0003] In order to effectively simulate and evaluate the working performance of the combustion chamber and its influence on the overall engine performance, the combustion chamber test machine has been widely used. The combustion process in the test machine needs to be accurately controlled and monitored to ensure the accuracy and reliability of the data. In view of the side effects of high-temperature combustion, such as equipment overheating and noise problems, the test machine is usually equipped with an exhaust water injection section for cooling. This cooling system not only helps to control the exhaust temperature, protect the test equipment and environment, but also improves the working conditions of the environment by reducing the noise during the test process.

[0004] The current cooling technology faces many challenges, including cooling efficiency, system integration and maintenance cost, which directly affect the performance and practicability of the combustion chamber test machine. Therefore, a aero -engine combustion chamber test machine cooling section spray device is proposed. SUMMARY

[0005] In order to overcome the shortcomings and deficiencies of the prior art, the utility model provides a aero -engine combustion chamber test machine cooling section spray device.

[0006] The technical scheme adopted by the utility model is a aero -engine combustion chamber test machine cooling section spray device, which comprises: a front flange, a rear flange, a large nozzle water injection ring unit and a small nozzle water injection ring unit;

[0007] The large nozzle water injection ring unit, the small nozzle water injection ring unit, the front flange and the rear flange are connected by bolts and then installed on the combustion chamber test machine for detachable integrated installation;

[0008] The inlets of the large nozzle water injection ring unit and the small nozzle water injection ring unit are independent of each other, which is used to select the cooling scheme according to the cooling requirement;

[0009] The small nozzle water injection ring unit is located near the combustion chamber outlet, which is used to achieve the maximum heat exchange function;

[0010] The water spraying ring unit with large nozzles and the water spraying ring unit with small nozzles are arranged at intervals of 10 nozzles, and the spray cone angle is between 30-45°, which is used to increase the contact area of the spray and hot air while achieving the widest spray coverage.

[0011] Further, the water spraying ring unit with small nozzles is composed of a water pipe connector, a fastening screw sleeve, a sleeve outer shell, a sleeve inner shell, a No. 1 positioning seat, a No. 1 lock cover, a spray pipe, a No. 2 positioning seat, a No. 2 lock cover, and a nozzle. The water spraying ring unit with large nozzles and the water spraying ring unit with small nozzles have the same structure and assembly method, except that the small nozzles are replaced by large nozzles.

[0012] Further, the front flange is a standard part with an outer diameter of 470 mm, an inner diameter of 288 mm, the rear flange has an outer diameter of 585 mm, an inner diameter of 272 mm, and a height of 170 mm.

[0013] Further, the sleeve outer shell and the sleeve inner shell are connected by a partition ring. The sleeve outer shell is a metal component with an inner diameter of 288 mm and an outer diameter of 312 mm, and the sleeve inner shell is a metal component with an inner diameter of 272 mm and an outer diameter of 278 mm.

[0014] Further, one end of the spray pipe is threadedly connected to the No. 1 positioning seat and then fixed by the No. 1 lock cover, the other end is threadedly connected to the No. 2 positioning seat and then fixed by the No. 2 lock cover, and the nozzle is threadedly connected to the spray pipe.

[0015] Further, the No. 2 positioning seat has an inner diameter of 34 mm and an outer diameter of 44 mm, the No. 2 lock cover is a matching part of the No. 2 positioning seat, the upper end of the No. 1 positioning seat has a diameter of 36 mm, the lower end has a width of 20 mm and a length of 36 mm, and the No. 1 lock cover is a matching part of the No. 1 positioning seat.

[0016] Further, the water spraying ring unit with large nozzles replaces the small nozzles with large nozzles, and the small nozzle matching part is used for inclined installation to the spray pipe. The total length of the small nozzle is 35 mm, the diameter is 14 mm, and the lower end opening is 3 mm. The total length of the large nozzle is 40 mm, the diameter is 22 mm, and the lower end opening is 5 mm.

[0017] Further, the small rotating flow core in the small nozzle has a total length of 28 mm, a right end length of 5 mm, a diameter of 10 mm, a middle segment of 15 mm, a diameter of 3 mm, and a lower end total length of 5 mm rotating flow structure with a 45° cutting. The large rotating flow core in the large nozzle has a total length of 334 mm, a right end length of 5 mm, a diameter of 18 mm, a middle segment of 20 mm, a diameter of 4 mm, and a lower end total length of 11 mm rotating flow structure with a 45° cutting.

[0018] Beneficial effects:

[0019] The utility model discloses a kind of aeroengine combustion chamber test machine cooling section spray device, the device is reduced the temperature of combustion chamber test machine wake by a series of innovative design, to protect test equipment and environment. Firstly, the device adopts five-layer independent water spraying system, this design allows to carry out accurate grading adjustment to cooling process, to adapt to different test conditions. Secondly, the layout of nozzle in device is carefully designed, so that the temperature reduction effect of combustion chamber test machine wake is remarkable, and it can reach 60% cooling effect according to test. In addition, nozzle included angle is specially treated, this design avoids the common thermal erosion phenomenon of general structure in high-temperature environment, prolongs the service life of device. Finally, the position of nozzle distance from central axis is specially set, compared with traditional device, this design makes cooling efficiency improve 20%. These improvements not only reduce the noise in test process, but also improve the working condition of environment, so that test process is safer and more efficient. In general, this cooling section spray device provides an effective solution for aeroengine combustion chamber test with its excellent cooling effect and environmental friendliness. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is the overall three-dimensional structure schematic diagram of the device;

[0021] Figure 2 It is the small nozzle water spraying ring unit structure schematic diagram of the device;

[0022] Figure 3 It is the large nozzle water spraying ring unit structure schematic diagram of the device;

[0023] Figure 4 It is the front flange and rear flange structure schematic diagram of the device;

[0024] Figure 5 It is the sleeve structure schematic diagram of the device;

[0025] Figure 6 It is the internal composition schematic diagram of the small nozzle water spraying ring unit of the device;

[0026] Figure 7 It is the internal composition schematic diagram of the large nozzle water spraying ring unit of the device;

[0027] Figure 8 It is the positioning seat and lock cover structure schematic diagram of the device;

[0028] Figure 9 It is the external structure schematic diagram of the small nozzle and large nozzle of the device;

[0029] Figure 10 It is the internal structure schematic diagram of the small nozzle and large nozzle of the device;

[0030] Figure 11The schematic diagram of the overall structure of the straight rod of the device. DETAILED DESCRIPTION

[0031] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the present application will be further described in detail below in combination with the drawings and specific embodiments.

[0032] As Figure 1 shown, an aero-engine combustion chamber test machine cooling section spray device, the device comprises: front flange 1, rear flange 2, large nozzle water ring unit 4, small nozzle water ring unit 3 composition;

[0033] Large nozzle water ring unit 4, small nozzle water ring unit 3, front flange 1 rear flange 2 through the bolt is connected to each other and then installed to the combustion chamber test machine, for carrying out detachable integrated installation;

[0034] Large nozzle water ring unit 4, small nozzle water ring unit 3 between the entrance independent of each other, for according to the cooling requirements to select the cooling scheme;

[0035] Small nozzle water ring unit 3 is located close to the combustion chamber outlet, for reaching the maximum heat exchange function;

[0036] Large nozzle water ring unit 4, small nozzle water ring unit 3 in the nozzle equidistant arrangement 10, spray cone angle between 30-45 °, for in reaching the spray coverage area is the largest at the same time, increase the spray and hot air contact area.

[0037] As Figure 2 and Figure 3 shown, the small nozzle water ring unit 3 by water pipe connector 5, fastening screw 6 sleeve, sleeve shell 7, sleeve inner shell 8, 1 number of positioning seat 9, 1 number of lock cover 10, spray pipe 11, 2 number of positioning seat 13, 2 number of lock cover 12, and nozzle 14 composition; large nozzle water ring unit 4 and small nozzle water ring unit 3 composition and assembly method is the same only to replace the small nozzle 14 for large nozzle 15.

[0038] As Figure 4 shown, the front flange 1 is a standard part with an outer diameter of 470 mm and an inner diameter of 288 mm; the rear flange 2 has an outer diameter of 585 mm, an inner diameter of 272 mm, and a height of 170 mm.

[0039] As Figure 5 shown, the sleeve outer shell 7 sleeve inner shell, 8 is connected through the ring, the sleeve outer shell 7 is a metal component with an inner diameter of 288 mm and an outer diameter of 312 mm, and the sleeve inner shell 8 is a metal component with an inner diameter of 272 mm and an outer diameter of 278 mm.

[0040] As Figure 6 and Figure 7As shown, the nozzle 11 is threadedly connected to the first positioning seat 9 and fixed by the first lock cover 10, and the other end is threadedly connected to the second positioning seat 13 and fixed by the second lock cover 12, and the nozzle 14 is threadedly connected to the nozzle 11.

[0041] As shown in the drawings, Figure 8 As shown, the second positioning seat 13 has an inner diameter of 34 mm and an outer diameter of 44 mm, the second lock cover 12 is a matching part of the second positioning seat 13, the upper end of the first positioning seat 9 has a diameter of 36 mm, the lower end has a width of 20 mm and a length of 36 mm, and the first lock cover 10 is a matching part of the first positioning seat 9.

[0042] As shown in the drawings, Figure 9 As shown, the large nozzle water spraying ring unit 4 replaces the small nozzle 14 with the large nozzle 15, and the small nozzle matching part 18 is used for inclined installation to the nozzle 11; the total length of the small nozzle 14 is 35 mm, the diameter is 14 mm, and the lower end opening is 3 mm; the total length of the large nozzle 15 is 40 mm, the diameter is 22 mm, and the lower end opening is 5 mm.

[0043] As shown in the drawings, Figure 10 As shown, the small swirl core 16 in the small nozzle 14 has a total length of 28 mm, a right end length of 5 mm, a diameter of 10 mm, a middle section of 15 mm, a diameter of 3 mm, and a lower end total length of 5 mm swirl structure with a 45° cutting; the large swirl core 17 in the large nozzle 15 has a total length of 334 mm, a right end length of 5 mm, a diameter of 18 mm, a middle section of 20 mm, a diameter of 4 mm, and a lower end total length of 11 mm swirl structure with a 45° cutting.

[0044] The large nozzle 15 and the small nozzle 14 both adopt a centrifugal structure, and the large nozzle 15 and the small nozzle 14 have simple structure and strong reliability, and are convenient for controlling the spray cone angle through structural design.

[0045] The cooling liquid of the large nozzle water spraying ring unit 4 and the small nozzle water spraying ring unit 3 enters the device through the water inlet, then enters from the lower end of the straight pipe, and finally flows into the nozzle, so as to achieve the effect of emptying the excess air in the system before forming stable spray.

[0046] The device is analyzed under the conditions of flow rate 0.3 kg / s, temperature 25℃, spray angle 70°, and speed 6 m / s, and the cooling effect of different particle diameters is analyzed: the particle diameter of about 0.08 mm-0.1 mm can achieve the best cooling effect.

[0047] Because of an ablation phenomenon in actual working condition, the main reason is that the middle of the small nozzle water spraying ring unit 3 is difficult to be cooled by the spray, so the hot air with high temperature and high pressure long-term burns the middle of the spraying ring, which is the weakest point of the whole structure. Therefore, in view of this problem, the position or angle of the nozzle needs to be adjusted, so that the sprayed spray can play a cooling effect on the middle of the spraying ring. Therefore, the normal angle of the small nozzle 14 is 30°. Therefore, the normal angle of the small nozzle 14 is 30°, when the nozzle angle is 30°, the spray is concentrated inward, and the cooling effect of the middle of the spraying ring is good, and when the nozzle angle is less than 30°, the sprayed cooling liquid is high in interference degree, resulting in a decrease in the contact area of the cooling liquid and the hot flow.

[0048] As shown in Figure 11 The first layer of the whole exhaust water spraying section, that is, the spray group, is subjected to the maximum pressure load, and when the combustion chamber flow pressure exceeds 4kPa, the nozzle part is prone to cracks. In order to reduce the adverse effects, tests show that the length of the short cross rod 19 is 25mm, the length of the middle cross rod 20 is 43mm, and the length of the long cross rod 21 is 50mm.

[0049] In the description of the present application, it should be explained that, unless otherwise specified and limited, the terms "arrangement", "installation", "connection", "connection", "fixing" should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0050] Although the embodiments of the present application have been shown and described, it can be understood by those skilled in the art that various equivalent changes, modifications, replacements and variations of the embodiments can be made without departing from the principles and spirits of the present application, and the scope of the present application is defined by the appended claims and their equivalent scope.

Claims

1. An aircraft engine combustor rig cooling section spray device characterized by The device comprises a front flange (1), a rear flange (2), a large nozzle water spraying ring unit (4), and a small nozzle water spraying ring unit (3). The large nozzle water spraying ring unit (4), the small nozzle water spraying ring unit (3), the front flange (1), and the rear flange (2) are connected by bolts and then installed on a combustion chamber test machine for detachable integrated installation. The large nozzle water spraying ring unit (4) and the small nozzle water spraying ring unit (3) are independently connected at the inlet for selecting a cooling scheme according to cooling requirements. The small nozzle water spraying ring unit (3) is located close to the outlet of the combustion chamber for achieving maximum heat exchange function. The large nozzle water spraying ring unit (4) and the small nozzle water spraying ring unit (3) are arranged at equal intervals with 10 nozzles, and the spray cone angle is between 30-45° for achieving the widest spray coverage while increasing the contact area between the spray and hot air.

2. An aircraft engine combustor rig cooling section spray device as recited in claim 1, wherein, The small nozzle water spraying ring unit (3) is composed of a water pipe connector (5), a fastening screw (6) sleeve, a sleeve outer shell (7), a sleeve inner shell (8), a No. 1 positioning seat (9), a No. 1 lock cover (10), a spray pipe (11), a No. 2 positioning seat (13), a No. 2 lock cover (12), and a nozzle (14). The large nozzle water spraying ring unit (4) has the same structure and assembly method as the small nozzle water spraying ring unit (3), except that the small nozzle (14) is replaced by a large nozzle (15).

3. An apparatus for testing a cooling section of a combustion chamber of a turbine engine as set forth in claim 1, characterized in that, The front flange (1) is a standard part with an outer diameter of 470 mm and an inner diameter of 288 mm. The rear flange (2) has an outer diameter of 585 mm, an inner diameter of 272 mm, and a height of 170 mm.

4. An aircraft engine combustor rig cooling section spray device as recited in claim 2, wherein, The sleeve outer shell (7) and the sleeve inner shell (8) are connected by a partition ring. The sleeve outer shell (7) is a metal component with an inner diameter of 288 mm and an outer diameter of 312 mm. The sleeve inner shell (8) is a metal component with an inner diameter of 272 mm and an outer diameter of 278 mm.

5. An aircraft engine combustor rig cooling section spray device as recited in claim 2 wherein, One end of the spray pipe (11) is threadedly connected to the No. 1 positioning seat (9) and then fixed by the No. 1 lock cover (10). The other end is threadedly connected to the No. 2 positioning seat (13) and then fixed by the No. 2 lock cover (12). The nozzle (14) is threadedly connected to the spray pipe (11).

6. An aircraft engine combustor rig cooling section spray device as recited in claim 2, wherein, The No. 2 positioning seat (13) has an inner diameter of 34 mm and an outer diameter of 44 mm. The No. 2 lock cover (12) is a mating part of the No. 2 positioning seat (13). The No. 1 positioning seat (9) has an upper end diameter of 36 mm, a lower end width of 20 mm, and a length of 36 mm. The No. 1 lock cover (10) is a mating part of the No. 1 positioning seat (9).

7. An aircraft engine combustor rig cooling section spray device as recited in claim 1, wherein, The large nozzle water spraying ring unit (4) replaces the small nozzle (14) with a large nozzle (15). The small nozzle mating part (18) is used for inclined installation on the spray pipe (11). The small nozzle (14) has a total length of 35 mm, a diameter of 14 mm, and a lower end opening of 3 mm. The large nozzle (15) has a total length of 40 mm, a diameter of 22 mm, and a lower end opening of 5 mm.

8. An aircraft engine combustor rig cooling section spray device as recited in claim 7, wherein, The total length of the small cyclone core (16) in the small nozzle (14) is 28 mm, the length of the right end is 5 mm, the diameter is 10 mm, the length of the middle section is 15 mm, the diameter is 3 mm, the total length of the lower end is 5 mm, and the cyclone structure is cut at 45°. The total length of the large cyclone core (17) in the large nozzle (15) is 334 mm, the length of the right end is 5 mm, the diameter is 18 mm, the length of the middle section is 20 mm, the diameter is 4 mm, the total length of the lower end is 11 mm, and the cyclone structure is cut at 45°.

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