An annular spray gun device for simulating the service environment of aircraft engine turbine blades

Abstract

The present invention discloses an annular spray gun device for simulating the service environment of an aircraft engine turbine blade, comprising a supersonic gas spray gun, an annular cavity, a flow collector, a rear end cover and a front end cover; the front and rear end surfaces of the annular cavity are respectively provided with a front end cover and a rear end cover, the flow collector is provided at the very center position inside the annular cavity, and the supersonic gas spray guns are evenly arranged on the circumferential surface position of the rear end cover; the supersonic gas spray gun is used to provide a near-real service environment of thermal coupling such as high temperature, erosion, corrosion, etc.; the supersonic gas spray gun sprays an atomized medium into the annular cavity, and after being ignited by an ignition plug, the annular cavity and the flow collector gather the ignited flame into a ring shape, and spray it out from the annular opening of the front end cover; the present invention can realize the simulation of the near-real service environment of thermal barrier coating of aircraft engine turbine blades such as high temperature, erosion, corrosion, etc. of thermal coupling, and provide an important platform for understanding the failure process and failure mechanism of high-temperature components in complex service environments.

Description

Technical Field

[0001] The invention belongs to the technical field of simulation of the service environment of thermal barrier coatings of aircraft engine turbine blades, and in particular relates to an annular spray gun device for simulating the service environment of aircraft engine turbine blades. Background Art

[0002] High-pressure turbine blades are the core components of aircraft engines that are most demanding in terms of temperature and load bearing, and are also the shortcoming that restricts the development of engines. Thermal barrier coating insulation technology is internationally recognized as the most practical way to significantly increase the service temperature of turbine blades.

[0003] Since thermal barrier coatings crack and peel off without warning, peeling failure is a key issue that needs to be urgently addressed for their safe application and development. In addition to the complex geometry, microstructure and performance differences between layers, the key factors that cause the failure of thermal barrier coatings are complex service environments such as high-temperature alternating thermal cycles, repeated impact of particles, and continuous erosion by corrosive gases. In order to clarify the failure mechanism of thermal barrier coatings in this service environment, the development of a near-real service environment simulation device is particularly important. This is because testing on actual engines is not only extremely expensive, but also makes it impossible to accurately decouple, control and recouple various environments and loads.

[0004] At present, in the simulation device of the service environment of thermal barrier coatings on aircraft engine turbine blades, Patent Publication No.: CN1818612A uses an independently developed thermal barrier coating thermal shock resistance test device to simulate single loads such as thermal shock in aircraft engines; Patent Publication No.: CN101644650A uses a heating gun to realize the thermal cycle performance test of thermal barrier coatings.

[0005] From the above, it can be seen that the existing simulation devices can only realize the service environment of single loads such as thermal shock and thermal fatigue of aircraft engines or simple thermal-mechanical coupling, and cannot simulate the complex service environment of aircraft engine turbine blades in the real service environment such as high temperature alternating thermal cycle, repeated impact of particles, and continuous erosion of corrosive gases.

[0006] Therefore, comprehensive and realistic simulation of the thermal-mechanical coupled service environment of high temperature, erosion and corrosion of turbine blade thermal barrier coatings is the key to understanding its failure mechanism, achieving its safe application and optimizing its design. Summary of the invention

[0007] In order to overcome the shortcomings of the above-mentioned prior art, the purpose of the present invention is to provide an annular spray gun device for simulating the service environment of aircraft engine turbine blades. The annular spray gun device can simulate the near-real service environment of thermal barrier coating of aircraft engine turbine blades with thermal coupling such as high temperature, erosion and corrosion, and provide an important platform for understanding the failure process and failure mechanism of high-temperature components in complex service environments.

[0008] In order to achieve the above object, the technical solution adopted by the present invention is:

[0009] An annular spray gun device for simulating the service environment of an aircraft engine turbine blade comprises a supersonic gas spray gun, an annular cavity, a flow collector, a rear end cover, and a front end cover;

[0010] The front end cover and the rear end cover are respectively arranged on the front and rear end surfaces of the annular cavity, a flow collector is arranged in the inner ring of the annular cavity, and the supersonic gas spray guns are evenly arranged on the circumferential surface of the rear end cover;

[0011] A supersonic gas spray gun is fixed on the rear end cover, and a through hole is provided at the position of the supersonic gas spray gun nozzle of the rear end cover. Atomized media from eight supersonic gas spray guns are sprayed into the annular cavity, ignited by the ignition plug, and then sprayed out from the annular port after being gathered and constrained by the annular cavity.

[0012] The supersonic gas spray gun is used to provide a near-real service environment with thermal coupling such as high temperature, erosion, corrosion, etc. The supersonic gas spray gun sprays the atomized medium into the annular cavity, and after being ignited by the ignition plug, the annular cavity and the concentrator gather the ignited flame into a ring shape and spray it out from the front end cover;

[0013] The nozzles of the eight supersonic gas spray guns on the rear end cover face the annular nozzle of the annular cavity;

[0014] During operation, the atomized medium is ejected from the nozzles of eight supersonic gas spray guns. After the atomized medium covering the entire cavity is ignited by the ignition plug, the flame is constrained by the annular cone-shaped cavity at the rear end and the annular cylinder-shaped cavity in the middle, and then further gathered and constrained by the annular cone-shaped cavity at the front end, and finally ejected from the annular nozzle;

[0015] This makes the flame more concentrated, the impact stronger, and closer to the service environment of the thermal barrier coating of turbine blades.

[0016] The bottom of the front end cover is detachably connected to the top of the support plate, and the bottom of the support plate is arranged on the base; the base, the rib plate and the support plate are used to support the annular cavity so that the central axis of the annular cavity is parallel to the horizontal plane of the base; the rear end cover is detachably connected to the supersonic gas spray gun;

[0017] The front and rear ends of the inner cavity of the annular cavity are shaped as annular cones, and the middle part is shaped as annular cylinder;

[0018] The rib plate is connected to the base, the annular cavity and the support plate by welding.

[0019] The base, ribs and support plates are made of metal materials. The base is in the shape of a rectangular parallelepiped, the ribs are right-angled ribs, the support plate is in the shape of a rectangular parallelepiped with right angles on both sides, and a small rectangular parallelepiped is opened at the center of the edge of the support plate to increase the strength of the support plate.

[0020] The annular cavity is an annular hollow structure composed of an outer thin wall and an inner thin wall of high-temperature alloy material. The annular hollow structure enables the circulating cooling water to take out the heat in the annular cavity. A concentrator is arranged at the center of the annular cavity to gather the flame into a ring shape. One end of the concentrator is fixed on the outer side of the edge of the middle circle of the rear end cover, and the other end is flush with the front end cover. The purpose is to make the flame ejected from the nozzle of the annular cavity parallel to the central axis of the annular cavity.

[0021] The atomized medium is sprayed into the cavity of the annular cavity. The flame ignited by the ignition plug is gathered and restrained by the shape of the concentrator and does not enter the concentrator.

[0022] The concentrator is a hollow structure composed of two layers of thin-walled high-temperature alloy materials, and the hollow structure can be cooled by circulating cooling water; the middle part of the concentrator is a ring-shaped cylindrical structure, and the front end is a conical structure, which can gather the flame into a ring shape and spray it from the nozzle; thus, the flame is more concentrated, the impact force is stronger, and it is closer to the service environment of the thermal barrier coating of the turbine blade;

[0023] The material of the rear end cover and the front end cover is a high-temperature alloy, and the shape of the rear end cover and the front end cover are both ring-shaped. Eight circular through holes are evenly arranged along the circumferential direction on the rear end cover for detachable connection with the supersonic gas spray gun; twelve circular through holes are evenly arranged on the edge of the front end cover for detachable connection with the support plate.

[0024] The top of the annular cavity is provided with a cooling water inlet, and the bottom is provided with a cooling water outlet. The cooling water inlet and the cooling water outlet are connected to one end of a quick-connect connector through threads, and the other end of the quick-connect connector is connected to the inlet and outlet of the chiller through a hose made of a high-temperature and high-pressure resistant material;

[0025] The annular cavity is connected with a cooling water inlet and a cooling water outlet; water flows into the space formed by two thin walls of the entire cavity for cooling.

[0026] The cooling water coming out of the chiller enters the hollow annular cavity through the cooling water inlet, then cools the annular cavity, and finally flows out through the cooling water outlet to take away the heat of the annular cavity.

[0027] The bottom central axis of the annular cavity is also provided with an oil outlet for discharging excess aviation kerosene in the annular cavity; two ignition plugs are symmetrically arranged in the middle and lower part of the annular cavity for igniting the atomized gas sprayed from the supersonic gas spray gun;

[0028] The atomized medium sprayed by eight supersonic gas spray guns fills the entire cavity of the annular cavity. After the ignition plug is ignited, the atomized medium in the entire cavity will burn.

[0029] The cooling water inlet and cooling water outlet are symmetrically welded on the rear end cover, and the cooling water inlet and cooling water outlet are connected to the cooling water pipe with a quick-plug connector;

[0030] When in use, cooling water flows into the hollow concentrator through two cooling water inlets to cool the concentrator, and then flows out through two cooling water outlets. The wall thickness of the entire concentrator is also composed of two thin walls, and water flows into the space composed of the two thin walls of the entire concentrator for cooling.

[0031] The supersonic gas spray gun includes an inner cavity, a fixed plate, a cyclone, and an atomizer; the inner cavity is in the shape of a hollow cylinder. Since it works at a high temperature, the inner cavity is made of a high-temperature alloy material. One end of the inner cavity is connected to the fixed plate, and the other end is connected to a high-pressure hose. The inner cavity gathers compressed air from the high-pressure hose.

[0032] A hollow channel is arranged on the cylindrical surface of the inner cavity, and a connecting plate is arranged at the other end of the hollow channel. The connecting plate is connected to the movable plate, and the connecting plate and the movable plate are rectangular parallelepiped with chamfered four corners. A powder channel is arranged on the movable plate, and the powder channel and the powder pipeline are connected with a quick-plug connector. The powder channel is used to provide erosion, corrosion particles or gaseous corrosive media. The powder channel is a bent pipe structure and the material is metal.

[0033] A fixed block is provided at the kerosene inlet, the fixed block is connected to the movable plate, and the fixed block is used to fix the kerosene channel; the materials of the connecting plate, the movable plate and the fixed block are high temperature alloys;

[0034] Erosion, corrosion particles or gaseous corrosive media enter the inner cavity from the powder channel, and then are ejected from the cyclone to the annular cavity with compressed air, and finally impact the surface of the thermal barrier coating of the turbine blade with the burning flame jet, thereby simulating the high temperature, erosion, corrosion and other thermal-mechanical coupled service environment of the thermal barrier coating of the aircraft engine turbine blade.

[0035] The fixing plate is made of high-temperature alloy material, the hole in the middle is cylindrical, and four through holes are evenly opened on the edge of the fixing plate, and the through holes are connected to the rear end cover bolts;

[0036] The material of the cyclone is high temperature alloy. Spiral curled blades are arranged at equal intervals around the cyclone. The spiral curled blades make the ejected compressed air form a swirling flow with rotation. There are small holes on the hub of the cyclone, which are connected to the inner cavity to increase the pressure of the compressed air. The outer side of the cyclone is detachably assembled and connected to one end of the inner cavity.

[0037] The compressed air is delivered to the inner cavity from the high-pressure hose, and then passes through the cyclone to generate a swirling flow with a rotational angle, while the air pressure is increased and sprayed into the annular cavity.

[0038] The atomizer is cylindrical, made of high-temperature alloy, and has nine small holes evenly arranged along the circumference, with a small hole in the middle, and the small holes are respectively connected to the kerosene channel and the kerosene inlet;

[0039] The atomizer is detachably connected to the inner side of the cyclone, the rear end of the cyclone is connected to one end of the kerosene channel, the other end of the kerosene channel is provided with a kerosene inlet, the kerosene inlet is threadedly connected to the kerosene hose, the atomizer atomizes the kerosene, and ignites it in the annular cavity through an ignition plug for thermal shock;

[0040] Kerosene enters from the kerosene inlet and is transported to the atomizer through the kerosene channel. The atomizer atomizes the kerosene and then sprays it out from the nozzle and is sprayed into the annular cavity together with the compressed air from the cyclone.

[0041] Beneficial effects of the present invention:

[0042] The present invention can simulate the near-real service environment of thermal barrier coating of aircraft engine turbine blades, such as high temperature, erosion, corrosion, etc., and realizes the simulation of complex service environments such as high temperature alternating thermal cycle, repeated impact of particles, and continuous erosion of corrosive gases in aircraft engines.

[0043] The annular cavity of the present invention makes the flame more concentrated and has a stronger impact force, which is closer to the service environment of the thermal barrier coating of turbine blades. It can simulate a single service environment such as high temperature, erosion, and corrosion, and can also simulate a complex service environment under the combined action of any two or three of them, making up for the defects of simulating a single service environment and not adding hard particle erosion at present.

[0044] The present invention has a complete erosion and corrosion medium loading system, which can be applied to both granular and gaseous corrosive media, and has an automatic and complete ignition system. The invention provides an important platform for effectively evaluating the failure process and failure mechanism of high-temperature components in a service environment with high-temperature thermal cycles, erosion and corrosion integration. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is the overall structural diagram of the annular spray gun device of the present invention.

[0046] Figure 2 It is a cross-sectional view of the annular spray gun device of the present invention.

[0047] Figure 3 It is a front view of the annular spray gun device of the present invention.

[0048] Figure 4 It is a rear side view of the annular spray gun device of the present invention.

[0049] Figure 5 It is a detailed diagram of the supersonic gas spray gun of the present invention.

[0050] Figure 6 This is a structural diagram of the cyclone of the present invention.

[0051] Figure 7 It is the structural diagram of the atomizer of the present invention. DETAILED DESCRIPTION

[0052] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0053] like Figure 1 As shown, an annular spray gun device for simulating the service environment of an aircraft engine turbine blade comprises a supersonic gas spray gun 1, an annular cavity 2, a flow collector 12, a rear end cover 3 and a front end cover 4. The supersonic gas spray gun 1 is detachably connected to the rear end cover 3, the front end cover 4 and the rear end cover 3 are welded to the front and rear end surfaces of the annular cavity 2, and the flow collector 12 is welded to the center of the annular cavity 2.

[0054] The supersonic gas spray gun 1 is used to provide a near-real service environment of thermal coupling such as high temperature, erosion, and corrosion; the supersonic gas spray gun 1 sprays the atomized medium into the annular cavity 2, and after being ignited by the ignition plug 11, the annular cavity 2 and the concentrator 12 gather the ignited flame into a ring shape, and spray it out from the annular opening of the front end cover 4, so that the flame is more concentrated, the impact force is stronger, and it is closer to the service environment of the thermal barrier coating of the turbine blade;

[0055] It also includes a base 5, a rib plate 6 and a support plate 7, one end of the support plate 7 is detachably connected to the front end cover 4, and the other end is welded to the base 5; the rib plate 6 is connected to the base 5, the annular cavity 2 and the support plate 7 by welding; the base 5, the rib plate 6 and the support plate 7 are used to support the annular cavity 2 so that the central axis of the annular cavity 2 is parallel to the horizontal plane of the base 5.

[0056] like Figure 2 As shown, the annular cavity 2 is an annular hollow structure composed of an outer thin wall 201 and an inner thin wall 202 of high temperature alloy material. This structure is to allow the circulating cooling water to take out the heat in the annular cavity 2; a concentrator 12 is welded at the center of the annular cavity 2 to gather the flame into a ring shape. One end of the concentrator 12 is welded and fixed at the center of the rear end cover 3, and the other end is flush with the front end cover 4, so that the flame sprayed from the nozzle of the annular cavity 2 is parallel to the central axis of the annular cavity 2;

[0057] The collector 12 is a hollow structure composed of two layers of thin-walled high-temperature alloy materials. The purpose of this structure is to cool the collector 12 by circulating cooling water. The middle part of the collector 12 is an annular cylindrical structure, and the front end is a conical structure. This structure can gather the flame into a ring shape and spray it out from the nozzle, so that the flame is more concentrated, the impact force is stronger, and it is closer to the service environment of the thermal barrier coating of the turbine blade.

[0058] like Figure 3 As shown, the rear end cover 3 and the front end cover 4 are made of high temperature alloy, and the shapes of the rear end cover 3 and the front end cover 4 are both ring-shaped. The rear end cover 3 is evenly arranged with eight round through holes along the circumferential direction for detachable connection with the supersonic gas spray gun 1; the edge of the front end cover 4 is evenly arranged with twelve round through holes for detachable connection with the support plate 7;

[0059] The base 5, ribs 6 and support plate 7 are made of metal materials. The base 5 is in the shape of a rectangular parallelepiped, the ribs 6 are right-angled ribs, and the support plate 7 is in the shape of a rectangular parallelepiped with right angles on both sides. At the same time, a small rectangular parallelepiped is opened at the center of the edge of the support plate 7 to increase the strength of the support plate 7;

[0060] A cooling water inlet 8 is welded on the top of the annular cavity 2, and a cooling water outlet 9 is welded on the bottom. The cooling water inlet 8 and the cooling water outlet 9 are connected to one end of a quick-connect connector through threads, and the other end of the quick-connect connector is connected to the inlet and outlet of the chiller through a hose made of high temperature and high pressure resistant material;

[0061] When in use, since the annular cavity 2 is a hollow structure composed of two thin walls, the entire annular cavity 2 is interconnected. The cooling water from the chiller enters the hollow annular cavity 2 through the cooling water inlet 8, then cools the annular cavity 2, and finally flows out through the cooling water outlet 9, thereby taking away the heat of the annular cavity 2;

[0062] An oil outlet 10 is welded on the bottom center axis of the annular cavity 2 for discharging excess aviation kerosene in the cavity; two ignition plugs 11 are symmetrically arranged in the middle and lower part of the annular cavity 2 for igniting the atomized gas sprayed from the supersonic gas spray gun 1.

[0063] The nozzles of the eight supersonic gas spray guns 1 on the rear end cover 3 face the annular nozzle of the annular cavity 2. The front and rear ends of the inner cavity of the annular cavity 2 are in the shape of annular cones, and the middle part is in the shape of annular cylinders.

[0064] During operation, the atomized medium is ejected from the nozzles of the eight supersonic gas spray guns 1. After the atomized medium covering the entire cavity is ignited by the ignition plug 11, the flame is constrained by the annular cone-shaped cavity at the rear end and the annular cylinder-shaped cavity in the middle, and then the flame is further gathered and constrained by the annular cone-shaped cavity at the front end, and finally ejected from the annular nozzle.

[0065] like Figure 4 As shown, a cooling water inlet 13 and a cooling water outlet 14 are symmetrically welded on the rear end cover 3, and the cooling water inlet 13 and the cooling water outlet 14 are connected to the cooling water pipe by a quick-insert connector;

[0066] When in use, cooling water flows into the hollow flow collector 12 through the two cooling water inlets 13 to cool the flow collector 12 , and then flows out through the two cooling water outlets 14 .

[0067] like Figure 5 As shown, the supersonic gas spray gun 1 includes an inner cavity 101, a fixing plate 102, a swirler 103, and an atomizer 104. The inner cavity 101 is in the shape of a hollow cylinder. Since it works at a high temperature, the inner cavity 101 is made of a high-temperature alloy material. One end of the inner cavity 101 is welded to the fixing plate 102, and the other end is threadedly connected to a high-pressure hose 105. The function of the inner cavity 101 is to gather the compressed air from the high-pressure hose 105.

[0068] A hollow channel 112 is welded on the cylindrical surface of the inner cavity 101, and a connecting plate 108 is welded on the other end of the hollow channel 112. The connecting plate 108 is bolted to the movable plate 109. The connecting plate 108 and the movable plate 109 are rectangular parallelepipeds with four chamfered right angles. A powder channel 107 is welded on the movable plate 109. The powder channel 107 is connected to the powder pipeline with a quick-insert connector. The powder channel 107 is used to provide erosion, corrosion particles or gaseous corrosive media;

[0069] The powder channel 107 is a bent pipe structure and is made of metal.

[0070] A fixing block 110 is welded at the kerosene inlet 106, and the fixing block 110 is bolted to the movable plate 109. The fixing block 110 is used to fix the kerosene channel 111. The materials of the connecting plate 108, the movable plate 109 and the fixing block 110 are high temperature alloys.

[0071] When in use, erosion, corrosion particles or gaseous corrosive media enter the inner cavity 101 from the powder channel 107, and then are ejected from the cyclone 103 to the annular cavity 2 with the compressed air, and finally are ejected with the burning flame to impact the surface of the thermal barrier coating of the turbine blade, so as to simulate the service environment of thermal coupling such as high temperature, erosion, and corrosion of the thermal barrier coating of the turbine blade of the aircraft engine;

[0072] The fixing plate 102 is made of high temperature alloy material, the hole in the middle is cylindrical, and four through holes are evenly opened on the edge of the fixing plate 102, which is used to be bolted to the rear end cover 3;

[0073] like Figure 6As shown, the material of the cyclone 103 is a high temperature alloy, and spirally curled blades are arranged around the cyclone 103, which is used to make the ejected compressed air form a swirl with a curl. A small hole is opened on the hub of the cyclone 103, and the small hole is communicated with the inner cavity 101, and its function is to increase the pressure of the compressed air. The outer side of the cyclone 103 is detachably assembled and connected to one end of the inner cavity 101;

[0074] When in use, compressed air is delivered from the high-pressure hose 105 to the inner cavity 101, and then passes through the cyclone 103 to generate a swirling flow with a rotational angle, and at the same time, the air pressure is increased and sprayed into the annular cavity 2;

[0075] like Figure 7 As shown, the atomizer 104 is cylindrical, made of high temperature alloy, and has nine small holes evenly arranged along the circumferential direction, with a small hole arranged in the middle, and the small holes are respectively connected to the kerosene channel 111 and the kerosene inlet 106;

[0076] The atomizer 104 is detachably connected to the inner side of the cyclone 103. The rear end of the cyclone 103 is connected to one end of the kerosene channel 111 by welding. The other end of the kerosene channel 111 is welded with a kerosene inlet 106, which is threadedly connected to a kerosene hose. The atomizer 104 is used to atomize the kerosene and ignite it in the annular cavity 2 through the ignition plug 11 for thermal shock.

[0077] When in use, kerosene enters from the kerosene inlet 106 and is transported to the atomizer 104 through the kerosene channel 111 . The atomizer 104 atomizes the kerosene and then sprays it out from the nozzle and is sprayed into the annular cavity 2 together with the compressed air from the cyclone 103 .

[0078] Working principle of the present invention:

[0079] During use, compressed air is delivered to each supersonic gas spray gun 1 from the high-pressure hose 105, and at the same time, aviation kerosene enters from the kerosene inlet 106 and is delivered to the atomizer 104 through the kerosene channel 111. The atomizer 104 atomizes the kerosene and then sprays it out from the nozzle, and erosion, corrosion particles or gaseous corrosive media enter each supersonic gas spray gun 1 from the powder channel 107, and the atomized aviation kerosene, erosion, corrosion particles or gaseous corrosive media are sprayed into the annular cavity 2 along with the compressed air. The atomized gas formed by the eight supersonic gas spray guns 1 fills the entire annular cavity 2, and then the two ignition plugs 11 in the annular cavity 2 ignite the atomized gas, and finally the condenser 12 gathers the flame into a ring shape and sprays it from the annular port of the front end cover 4 to impact the thermal barrier coating of the turbine blade, so as to achieve a service environment of thermal coupling such as high temperature, erosion, corrosion, etc. of the thermal barrier coating of the aircraft engine turbine blade. During the entire operation process, cooling water is constantly circulating and cooling the annular spray gun device.

Claims

1. An annular spray gun device for simulating the service environment of an aircraft engine turbine blade, characterized in that: It comprises a supersonic gas spray gun (1), an annular cavity (2), a flow collector (12), a rear end cover (3), and a front end cover (4); The front end cover (4) and the rear end cover (3) are respectively arranged on the front and rear end surfaces of the annular cavity (2); a flow collector (12) is arranged in the inner ring of the annular cavity (2); and the supersonic gas spray guns (1) are evenly arranged on the circumferential surface of the rear end cover (3); The supersonic gas spray gun (1) is used to provide a near-real service environment with thermal coupling such as high temperature, erosion, corrosion, etc. The supersonic gas spray gun (1) sprays the atomized medium into the annular cavity (2), and after being ignited by the ignition plug (11), the annular cavity (2) and the condenser (12) gather the ignited flame into a ring shape and spray it out from the front end cover (4); The supersonic gas spray gun (1) comprises an inner cavity (101), a fixing plate (102), a swirler (103), and an atomizer (104); the inner cavity (101) is in the shape of a hollow cylinder, the inner cavity (101) is made of a high-temperature alloy material, one end of the inner cavity (101) is connected to the fixing plate (102), and the other end is connected to a high-pressure hose (105), and the inner cavity (101) gathers compressed air from the high-pressure hose (105); A hollow channel (112) is provided on the cylindrical surface of the inner cavity (101), and a connecting plate (108) is provided at the other end of the hollow channel (112), the connecting plate (108) is connected to a movable plate (109), the connecting plate (108) and the movable plate (109) are rectangular parallelepipeds with four chamfered right angles, a powder channel (107) is provided on the movable plate (109), the powder channel (107) is connected to the powder pipeline by a quick-plug connector, the powder channel (107) is used to provide erosion, corrosion particles or gaseous corrosive media, the powder channel (107) is a bent pipe structure, and the material is metal; A fixed block (110) is provided at the kerosene inlet (106), the fixed block (110) is connected to the movable plate (109), and the fixed block (110) is used to fix the kerosene channel (111); the material of the connecting plate (108), the movable plate (109) and the fixed block (110) is a high temperature alloy; Erosion and corrosion particles or gaseous corrosive media enter the inner cavity (101) from the powder channel (107), are then ejected from the cyclone (103) to the annular cavity (2) along with the compressed air, and finally impact the surface of the thermal barrier coating of the turbine blade along with the burning flame, thereby simulating the thermal-mechanical coupled service environment of the thermal barrier coating of the aircraft engine turbine blade with high temperature, erosion and corrosion.

2. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The front end cover (4) is arranged on the base (5) via a support plate (7); The base (5), the rib plate (6) and the support plate (7) are used to support the annular cavity (2) so that the central axis of the annular cavity (2) is parallel to the horizontal plane; the rear end cover (3) is detachably connected to the supersonic gas spray gun (1); The front and rear ends of the inner cavity of the annular cavity (2) are shaped like annular cones, and the middle part is shaped like an annular cylinder. Atomized medium is ejected from nozzles of eight supersonic gas spray guns (1). After the atomized medium covering the entire cavity is ignited by an ignition plug (11), the flame is constrained by the annular cone-shaped cavity at the rear end and the annular cylinder-shaped cavity in the middle, and then the flame is further gathered and constrained by the annular cone-shaped cavity at the front end, and finally ejected from the annular nozzle.

3. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The annular cavity (2) is an annular hollow structure composed of an outer thin wall (201) and an inner thin wall (202) of high-temperature alloy material. The annular hollow structure enables circulating cooling water to remove heat from the annular cavity (2). A concentrator (12) is provided at the exact center of the annular cavity (2) for concentrating flames into a ring shape. One end of the concentrator (12) is fixed to the edge of the middle circle of the rear end cover (3) and the other end is flush with the front end cover (4), so that the flame ejected from the nozzle of the annular cavity (2) is parallel to the central axis of the annular cavity (2).

4. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The concentrator (12) is a hollow structure composed of two layers of thin-walled high-temperature alloy material, and the hollow structure can cool the concentrator (12) through circulating cooling water; the middle part of the concentrator (12) is an annular cylindrical structure, and the front end is a conical structure, and the conical structure can gather the flame into a ring shape and spray it out from the nozzle.

5. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The rear end cover (3) and the front end cover (4) are made of high temperature alloy, and are both in the shape of a circular ring. The rear end cover (3) is provided with eight circular through holes evenly arranged along the circumferential direction, and is used for detachably connecting with the supersonic gas spray gun (1); A cooling water inlet (13) and a cooling water outlet (14) are symmetrically welded on the rear end cover (3), and the cooling water inlet (13) and the cooling water outlet (14) are connected to the cooling water pipe by using a quick-insert connector; The cooling water flows into the hollow flow collector (12) through two cooling water inlets (13), cools the flow collector (12), and then flows out through two cooling water outlets (14).

6. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The annular cavity (2) is provided with a cooling water inlet (8) at the top and a cooling water outlet (9) at the bottom. The cooling water inlet (8) and the cooling water outlet (9) are connected to one end of a quick-connect connector via threads, and the other end of the quick-connect connector is connected to the inlet and outlet of the chiller via a hose made of a high-temperature and high-pressure resistant material. The annular cavity (2) is in communication with a cooling water inlet (8) and a cooling water outlet (9); The cooling water from the chiller enters the hollow annular cavity (2) through the cooling water inlet (8), then cools the annular cavity (2), and finally flows out through the cooling water outlet (9), thereby taking away the heat of the annular cavity (2).

7. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: An oil outlet (10) is also provided on the central axis of the bottom of the annular cavity (2) for discharging excess aviation kerosene in the annular cavity (2); two ignition plugs (11) are symmetrically provided in the middle and lower part of the annular cavity (2) for igniting the atomized gas sprayed from the supersonic gas spray gun (1).

8. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The fixing plate (102) is made of a high-temperature alloy material, the hole in the middle is in a cylindrical shape, four through holes are evenly opened on the edge of the fixing plate (102), and the through holes are connected to the rear end cover (3) by bolts; The cyclone (103) is made of a high-temperature alloy. Spirally curled blades are arranged at equal intervals around the cyclone (103). The spirally curled blades cause the ejected compressed air to form a swirling flow with a curl. A small hole is opened on the hub of the cyclone (103). The small hole is connected to the inner cavity (101) to increase the pressure of the compressed air. The outer side of the cyclone (103) is detachably assembled and connected to one end of the inner cavity (101). Compressed air is delivered to the inner cavity (101) from a high-pressure hose (105), and then passes through a swirler (103) to generate a swirling flow, while increasing the air pressure and spraying it into the annular cavity (2).

9. The annular spray gun device for simulating the service environment of an aircraft engine turbine blade according to claim 1, characterized in that: The atomizer (104) is cylindrical and made of high-temperature alloy. Nine small holes are evenly arranged along the circumference, and a small hole is arranged in the middle. The small holes are respectively connected to the kerosene channel (111) and the kerosene inlet (106); The atomizer (104) is detachably connected to the inner side of the cyclone (103); the rear end of the cyclone (103) is connected to one end of the kerosene channel (111); the other end of the kerosene channel (111) is provided with a kerosene inlet (106); the kerosene inlet (106) is threadedly connected to a kerosene hose; the atomizer (104) atomizes the kerosene, which is ignited by an ignition plug (11) in the annular cavity (2) to perform thermal shock; Kerosene enters from the kerosene inlet (106) and is transported to the atomizer (104) through the kerosene channel (111). The atomizer (104) atomizes the kerosene and then sprays it out from the nozzle and is sprayed into the annular cavity (2) together with the compressed air from the cyclone (103).

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