A test device for coupling an interstage combustion chamber with oblique injection annular flow and low-pressure turbine guide vanes

Abstract

The present invention discloses a test device for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection circulation, which relates to the technical field of aero-engine experimental devices, including a combustion chamber test section and a guide vane test section, wherein the guide vane test section is fixedly connected to the inner and outer casings of the combustion chamber test section by flanges and screws, and the other end of the guide vane test section is fixedly connected to the tail gas section by flanges and screws. The present invention discloses a test device for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection circulation, which prolongs the residence time of the fuel in the combustion chamber, improves the combustion efficiency, and realizes the interstage combustion chamber design concept of aerodynamic organization by extending the injection piece into the flame tube at a certain angle to supply oil, and arranging oblique holes for air intake at various parts of the flame tube; and arranging temperature sensors, pressure sensors and flue gas analysis devices for data collection, which is of great significance for analyzing the relevant performance indicators of the coupling between the interstage combustion chamber and the low-pressure turbine guide vane with an oblique injection circulation.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine experimental devices, and in particular to an oblique-injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling experimental device. Background Art

[0002] The current design goals for advanced aircraft engines / gas turbines in the world are mainly focused on high compression ratio, high turbine inlet temperature, high thrust-to-mass ratio, low fuel consumption, high reliability and long life; and from the Brayton cycle principle, it can be seen that increasing the turbine inlet temperature and the total compression ratio of the engine can effectively improve the performance of the engine; the current compressor total pressure ratio and turbine inlet temperature have been greatly improved compared to the 1960s; but the engine turbine inlet total temperature is limited by the high temperature resistance of the turbine material and cannot be significantly improved; and in order to achieve supersonic flight, the mainstream improvement plan is to add an afterburner to the aircraft engine to increase the engine thrust.

[0003] The use of afterburners can greatly increase the engine's unit mass flow rate thrust and thrust-to-weight ratio, comprehensively improve the aircraft's maneuverability, expand the flight envelope, and enhance air control capabilities; but the afterburner essentially gains the advantage of increasing the engine's thrust-to-weight ratio at the expense of specific impulse, or fuel economy, and the afterburner has more serious infrared radiation, which is not conducive to the aircraft's stealth.

[0004] Through ideal cycle analysis of aircraft engines equipped with interstage combustion chambers, it can be seen that the installation of interstage combustion chambers can increase the engine unit thrust and reduce the size of the engine while keeping the existing compressor total pressure ratio, turbine inlet total temperature, and fuel consumption rate approximately unchanged.

[0005] The interstage combustion chamber can improve the unit thrust and thermal efficiency of the engine without changing the existing compressor total pressure ratio and turbine inlet total temperature, and under the condition of the same fuel consumption rate, to meet the aircraft's demand for aviation engines. And under the condition of maintaining the original thrust, the temperature of the main combustion chamber can be reduced, thereby reducing NOx emissions and reducing pollution. This means that the interstage combustion chamber does not rely on the limitation of the total temperature before the turbine and has low infrared radiation. It can meet the needs of stealth and manufacturing on the basis of improving engine performance, and has broad prospects and advantages.

[0006] The airflow velocity in the turbine transition section where the interstage combustion chamber is located is high and the space is limited, so it is difficult to organize combustion in the transition section. At the same time, after adding an interstage combustion chamber between the high-pressure and low-pressure turbines, the relevant research on the influence of interstage combustion on the low-pressure turbine guide vanes is still shallow. Therefore, it is urgent to design an interstage combustion chamber and low-pressure turbine guide vane coupling test device with oblique injection circulation, and use circumferential circulation technology to increase the residence time of the flame in a limited space to make the combustion more complete; on this basis, pay attention to the coupling matching law of interstage combustion and turbine guide vanes, and realize the relevant performance tests of interstage combustion and low-pressure turbine coupling, which has become a problem that technicians in this field need to solve urgently. Summary of the invention

[0007] The purpose of the present invention is to provide a test device for coupling an interstage combustion chamber with oblique injection and annular flow and a low-pressure turbine guide vane, so as to solve the problems listed in the background technology.

[0008] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0009] The present invention discloses an oblique injection circulation interstage combustion chamber and low-pressure turbine guide vane coupling test device, comprising a combustion chamber test section and a guide vane test section, wherein the guide vane test section is fixedly connected to the inner and outer casings of the combustion chamber test section by flanges and screws, and the other end of the guide vane test section is fixedly connected to the exhaust section by flanges and screws.

[0010] Preferably, the combustion chamber test section comprises a bluff body inner casing, a diffuser outer casing, a quartz glass observation window and a bluff body cooling air duct, the bluff body inner casing is fixedly connected to the inner wall of the diffuser outer casing, the leading edge bluff body of the bluff body inner casing is close to one end opening of the diffuser outer casing, the diffuser outer casing is a profile structure, and an oblique jet annular flow interstage combustion chamber flame tube is installed between the opposite surfaces of the bluff body inner casing and the diffuser outer casing;

[0011] The quartz glass observation windows are evenly distributed around the circumference and are fastened to the diffuser outer casing. One end of the bluff body cooling air pipe extends into the bluff body inner casing. The middle part of the bluff body cooling air pipe is tightly sealed with the side wall of the bluff body inner casing through a graphite gasket. The other end of the bluff body cooling air pipe is fastened to the outer side wall of the diffuser outer casing through a screw.

[0012] Combustion chamber outlet measuring thermocouples are installed on the flange of the diffuser outer casing and the outer flange of the oblique injection annular flow interstage combustion chamber flame tube, and the combustion chamber outlet measuring thermocouples are located downstream of the combustion chamber outlet of the oblique injection annular flow interstage combustion chamber flame tube;

[0013] A fuel injection component is fixedly mounted on the outer side wall of the diffuser outer casing through a pressure plate and a copper gasket, and a fuel injection port of the fuel injection component is located at the combustion chamber inlet of the oblique injection annular flow interstage combustion chamber flame tube.

[0014] Preferably, it also includes an incoming static pressure measuring tube, an incoming total pressure measuring tube, an incoming temperature measuring thermocouple and an igniter, wherein the incoming static pressure measuring tube is welded to the side wall of the diffuser outer casing; the incoming total pressure measuring tube is fixedly connected to the diffuser outer casing by a copper gasket and a screw; the incoming temperature measuring thermocouple is sealed to the side wall of the diffuser outer casing; the igniter passes through the diffuser outer casing and the oblique-injection circulating flow interstage combustion chamber flame tube, and the ignition end of the igniter extends into the oblique-injection circulating flow interstage combustion chamber flame tube.

[0015] Preferably, the guide vane test section includes a guide vane disc assembly, a guide vane outlet total pressure measurement rake, a guide vane outlet temperature measurement thermocouple, a guide vane cooling air intake ring pipe, a guide vane test section support plate and a support plate cooling water spray rod, and the guide vane disc assembly is engaged and connected with the inner tube of the guide vane test section through a boss clamping tooth;

[0016] The guide vane outlet total pressure measuring rake is sealed and connected to the outer tube of the guide vane test section through a copper gasket and a screw, and one end of the guide vane outlet total pressure measuring rake abuts against the outer side wall of the inner tube of the guide vane test section;

[0017] The guide vane outlet temperature measuring thermocouple passes through the outer tube of the guide vane test section and abuts against the outer side wall of the inner tube of the guide vane test section;

[0018] The guide vane cooling air intake ring pipe is installed on the outer side of the outer pipe of the guide vane test section, and the guide vane cooling air intake ring pipe passes through the outer pipe of the guide vane test section and is connected with the guide vane disc assembly;

[0019] The guide vane test section support plate is fixedly installed between the outer tube of the guide vane test section and the opposite surface of the inner tube of the guide vane test section, and the cross section of the guide vane test section support plate is in a water drop shape;

[0020] The support plate cooling water spray rod passes through the outer tube of the guide vane test section, and the support plate cooling water spray rod is located upstream of the guide vane test section support plate. The support plate cooling water spray rod sprays water on the circumferential section to cool the guide vane test section support plate.

[0021] Preferably, the exhaust section comprises a cooling cone and an exhaust section outer casing, the cooling cone is evenly provided with cooling holes in a circumferential direction, the cooling holes are connected to the bluff cooling air pipe, and the cooling cone is fixedly connected to the inner tube of the guide vane test section by screws;

[0022] The cross section formed by the tail gas section outer casing profile and the cold air cone profile gradually increases, and the tail gas section outer casing is fixedly connected to the outer tube of the guide vane test section by screws.

[0023] Preferably, the oblique injection annular flow interstage combustion chamber flame tube comprises a nozzle protection sleeve, a wall oblique hole, a front section mixing hole, a middle section mixing hole, and a rear section mixing hole, the axis of the nozzle protection sleeve forms a certain angle with the radial direction of the plane where it is located, and air film cooling holes are uniformly opened circumferentially on the side wall surface of the nozzle protection sleeve;

[0024] The wall inclined holes are all at certain angles to the radial direction and the axial direction, so as to organize the circumferential flow of the airflow in the flame tube of the oblique injection annular flow interstage combustion chamber;

[0025] The front section mixing hole is located downstream of the main combustion zone of the flame tube of the oblique injection annular flow interstage combustion chamber;

[0026] The middle section mixing hole is located in the middle of the nozzle protection sleeve; the rear section mixing hole is located at the bottom of the nozzle protection sleeve, and the rear section mixing hole is designed with an air duct structure.

[0027] Preferably, the guide vane disc assembly comprises a single guide vane component and a guide vane base, and the single guide vane component is evenly embedded along the circumference of the guide vane base through a latching tooth structure.

[0028] Preferably, a cold air inlet cavity is provided in the main body of the single guide vane component, a guide vane cold air hole is provided on the main body of the single guide vane component, and the guide vane cold air hole is communicated with the cold air inlet cavity;

[0029] A wall thermocouple wire measurement hole is also provided on the side surface of the main body of the single guide vane component;

[0030] A cold air ring cavity baffle is installed at one end of the main body of the single guide vane component.

[0031] Preferably, the guide vane outlet total pressure measuring rake includes a cooling circulating water inlet pipe, a cooling circulating water outlet pipe, a total pressure measuring point and a total pressure test connecting pipe. The cooling circulating water inlet pipe is connected to the cooling circulating water outlet pipe, and the total pressure measuring point and the total pressure test connecting pipe cooperate to measure the multi-point average total pressure of the incoming flow.

[0032] Compared with the prior art, the beneficial technical effects of the present invention are:

[0033] 1) On the wall of the combustion chamber flame tube, there are evenly distributed cooling air intake holes set at a certain angle to the axial direction and the radial direction. While providing air intake for the combustion chamber, it also provides circumferential kinetic energy and prolongs the gas residence time, which can greatly improve the combustion efficiency in the compact space of the interstage combustion chamber.

[0034] 2) The installation angle of the nozzle in the fuel injection part is consistent with the direction of circumferential circulation, which helps to enhance the mixing of kerosene and can also greatly increase the cross-flame speed.

[0035] 3) The interaction between the front mixing holes of the combustion chamber flame tube will produce a low-speed reflow zone on the axial section, which is conducive to the stability of the flame. The rear mixing holes extend into the flame tube in the form of an air bleed pipe, which enhances the penetration depth of the mixed gas and makes the outlet temperature field more uniform.

[0036] 4) The interstage combustion chamber is directly coupled with the low-pressure turbine guide vane, and coupled hot tests can be performed. The combustion chamber outlet temperature and pressure, the low-pressure turbine guide vane outlet temperature and pressure, the combustion chamber outlet flue gas composition, and the low-pressure turbine guide vane wall temperature can all be measured, which can be used to test the combustion performance of the interstage combustion chamber and the low-pressure turbine guide vane.

[0037] 5) The design of the interstage combustion chamber casing of the oblique injection circulation integrates the diffuser and the air intake section, which saves space and reduces pressure loss, which is of great significance for achieving a high-efficiency and low-resistance interstage combustion chamber design. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The present invention will be further described below in conjunction with the accompanying drawings.

[0039] Figure 1 It is a half-section view of a test device for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection annular flow according to the present invention;

[0040] Figure 2 It is a schematic diagram of the overall structure of an oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test device of the present invention;

[0041] Figure 3 is a half-section view of a combustion chamber test section of the present invention;

[0042] Figure 4 It is an overall structural view of the combustion chamber test section of the present invention;

[0043] Figure 5 It is a schematic diagram of the arrangement of the measuring points of the combustion chamber outlet temperature and the total pressure of the combustion chamber test section of the present invention;

[0044] Figure 6 It is a schematic diagram of the installation position of the combustion chamber fuel system and the igniter of the present invention;

[0045] Figure 7 It is a schematic diagram of the oblique injection annular flow interstage combustion chamber flame tube of the combustion chamber test section of the present invention;

[0046] Figure 8 is a partial cross-sectional view of a guide vane test section of the present invention;

[0047] Fig. 9 is a half-section view of a guide vane test section of the present invention;

[0048] Fig.10 is an overall view of the guide vane plate assembly of the present invention;

[0049] Fig.11 is an overall detailed view of a single component of a guide vane of the present invention;

[0050] Fig.12 is a half-section view of a guide vane outlet total pressure measuring rake of the present invention;

[0051] Fig.13 It is a half-section view of the tail gas section of the present invention.

[0052] Description of the accompanying drawings: 1. Combustion chamber test section; 101. Blunt body inner casing; 102. Diffuser outer casing; 103. Quartz glass observation window; 104. Blunt body cooling air pipe; 105. Oblique injection annular flow interstage combustion chamber flame tube; 106. Combustion chamber outlet measurement thermocouple; 107. Fuel injection component; 108. Incoming flow static pressure measurement tube; 109. Incoming flow total pressure measurement tube; 110. Incoming flow temperature measurement thermocouple; 111. Ignitor; 1051. Nozzle protection sleeve; 1052. Wall oblique hole; 1053. Front section mixing hole; 1054. Middle section mixing hole; 1055. Rear section mixing hole;

[0053] 2. Guide vane test section; 201. Guide vane disc assembly; 202. Guide vane outlet total pressure measurement rake; 203. Guide vane outlet temperature measurement thermocouple; 204. Guide vane cooling air intake ring pipe; 205. Guide vane test section support plate; 206. Support plate cooling water spray rod; 2011. Single guide vane component; 2012. Guide vane base; 2021. Cooling circulating water inlet pipe; 2022. Cooling circulating water outlet pipe; 2023. Total pressure measurement point; 2024. Total pressure test connecting pipe; 20111. Guide vane cold air hole; 20112. Cold air inlet cavity; 20113. Wall thermocouple wire measurement hole; 20114. Cold air ring cavity baffle;

[0054] 3. Exhaust section; 301. Cooling cone; 302. Exhaust section outer casing. DETAILED DESCRIPTION

[0055] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0056] like Figure 1-13 As shown, a test device for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection circulation includes a combustion chamber test section 1 and a guide vane test section 2. The guide vane test section 2 is fixedly connected to the inner and outer casings of the combustion chamber test section 1 by flanges and screws, and the other end of the guide vane test section 2 is fixedly connected to the exhaust section 3 by flanges and screws.

[0057] like Figure 3-4 As shown, the combustion chamber test section 1 includes a bluff body inner casing 101, a diffuser outer casing 102, a quartz glass observation window 103 and a bluff body cooling air pipe 104, the bluff body inner casing 101 is fixedly connected to the inner wall of the diffuser outer casing 102, the leading edge bluff body of the bluff body inner casing 101 is close to one end opening of the diffuser outer casing 102, the diffuser outer casing 102 has a special profile structure, the airflow is not easy to separate during the flow, and the incoming flow is diffused, reducing the total pressure loss of the combustion chamber; an oblique injection annular flow interstage combustion chamber flame tube 105 is installed between the opposite surfaces of the bluff body inner casing 101 and the diffuser outer casing 102;

[0058] The quartz glass observation windows 103 are evenly distributed and fastened on the diffuser outer casing 102, and five quartz glass observation windows 103 are evenly opened in the circumference. One end of the bluff body cooling air pipe 104 extends into the bluff body inner casing 101. The middle part of the bluff body cooling air pipe 104 is pressed and sealed with the side wall of the bluff body inner casing 101 through a graphite gasket. The other end of the bluff body cooling air pipe 104 is fastened and connected with the outer side wall of the diffuser outer casing 102 through screws.

[0059] A combustion chamber outlet measuring thermocouple 106 is installed on the flange of the diffuser outer casing 102 and the outer flange of the oblique jet annular flow interstage combustion chamber flame tube 105, and the combustion chamber outlet measuring thermocouple 106 is located downstream of the combustion chamber outlet of the oblique jet annular flow interstage combustion chamber flame tube 105, and the combustion chamber outlet measuring thermocouple 106 is arranged in two of the five circumferential periods of 72°, wherein in one period, three thermocouples are distributed at intervals of 25° and their starting positions are 11° apart from the 72° period boundary, and in one period, four thermocouples are distributed at intervals of 24° and their starting positions are at the 72° period boundary;

[0060] A fuel injection component 107 is fixedly installed on the outer wall of the diffuser outer casing 102 through a pressure plate and a copper gasket, and the fuel injection port of the fuel injection component 107 is located at the combustion chamber inlet of the oblique injection annular interstage combustion chamber flame tube 105. There are five fuel injection components 107 evenly arranged in the circumference, and the nozzle direction forms an angle of 45° with the radial direction of the cross section.

[0061] Specifically, it also includes an incoming static pressure measuring tube 108, an incoming total pressure measuring tube 109, an incoming temperature measuring thermocouple 110 and an igniter 111. The incoming static pressure measuring tube 108 is welded to the side wall of the diffuser outer casing 102; the incoming total pressure measuring tube 109 is fixedly connected to the diffuser outer casing 102 through a copper gasket and screws; the incoming temperature measuring thermocouple 110 is sealed and connected to the side wall of the diffuser outer casing 102; the igniter 111 passes through the diffuser outer casing 102 and the oblique injection circulating flow interstage combustion chamber flame tube 105, and the ignition end of the igniter 111 extends into the oblique injection circulating flow interstage combustion chamber flame tube 105.

[0062] Specifically, the guide vane test section 2 includes a guide vane disc assembly 201, a guide vane outlet total pressure measurement rake 202, a guide vane outlet temperature measurement thermocouple 203, a guide vane cooling air intake ring pipe 204, a guide vane test section support plate 205 and a support plate cooling water spray rod. The guide vane disc assembly 201 is engaged and connected with the inner tube of the guide vane test section 2 through the boss clamping teeth to prevent rotation due to circumferential force;

[0063] The guide vane outlet total pressure measuring rake 202 is sealed and connected to the outer tube of the guide vane test section 2 through a copper gasket and a screw, and one end of the guide vane outlet total pressure measuring rake 202 abuts against the outer side wall of the inner tube of the guide vane test section 2;

[0064] The guide vane outlet temperature measuring thermocouple 203 penetrates the outer tube of the guide vane test section 2 and abuts against the outer side wall of the inner tube of the guide vane test section 2;

[0065] The guide vane cooling air intake ring pipe 204 is installed on the outer side of the outer pipe of the guide vane test section 2, and the guide vane cooling air intake ring pipe 204 penetrates the outer pipe of the guide vane test section 2 to provide cooling air for the guide vane disc assembly 201;

[0066] The guide vane test section support plate 205 is fixedly installed between the outer tube of the guide vane test section 2 and the opposite surface of the inner tube of the guide vane test section 2 to ensure the structural strength of the guide vane test section 2, and the cross section of the guide vane test section support plate 205 is in a water drop shape;

[0067] The support plate cooling water spray rod 206 passes through the outer tube of the guide vane test section 2, and the support plate cooling water spray rod 206 is located upstream of the guide vane test section support plate 205. The support plate cooling water spray rod 206 sprays water on the circumferential section to cool down the guide vane test section support plate 205.

[0068] Specifically, the exhaust section 3 includes a cooling cone 301 and an exhaust section outer casing 302. The cooling cone 301 is evenly provided with cooling holes in a circumferential direction. The cooling holes are connected to the bluff cooling air pipe 104 and discharge the air introduced into the bluff cooling air pipe 104. The cooling cone 301 is fixedly connected to the inner tube of the guide vane test section 2 by screws.

[0069] The cross section formed by the profile of the exhaust section outer casing 302 and the profile of the cold air cone 301 gradually increases, which plays a role in reducing the pressure of the exhaust gas. The exhaust section outer casing 302 is fixedly connected to the outer tube of the guide vane test section 2 by screws.

[0070] Specifically, the oblique injection annular flow interstage combustion chamber flame tube 105 includes a nozzle protection sleeve 1051, a wall oblique hole 1052, a front mixing hole 1053, a middle mixing hole 1054, and a rear mixing hole 1055. The axis of the nozzle protection sleeve 1051 forms an angle of 45° with the radial direction of the plane where it is located, and air film cooling holes with a diameter of 0.5 mm are uniformly opened on the side wall surface in a circumferential direction, and an oil outlet hole and a swirl sweeper are provided on the head;

[0071] The wall inclined holes 1052 are all at an angle of 30° to the axial direction and 45° to the radial direction, so as to organize the circumferential flow of the airflow in the oblique injection annular flow interstage combustion chamber flame tube 105;

[0072] The front section mixing hole 1053 is located downstream of the main combustion zone of the oblique injection annular flow interstage combustion chamber flame tube 105 and is used for air supplement and mixing;

[0073] The middle section mixing hole 1054 is located in the middle of the nozzle protective sleeve 1051 and is used for mixing cooling combustion gas; the rear section mixing hole 1055 is located at the bottom of the nozzle protective sleeve 1051, and the rear section mixing hole 1055 is designed with an air bleed pipe structure, so that the penetration depth of the mixed gas is greater, which will make the outlet temperature field more uniform.

[0074] Specifically, the guide vane disc assembly 201 includes a single guide vane component 2011 and a guide vane base 2012. The single guide vane component 2011 is evenly distributed and engaged with the guide vane base 2012 in the circumferential direction through a latching tooth structure. Furthermore, 30 single guide vane components are evenly distributed in the circumferential direction.

[0075] Specifically, a cold air inlet cavity 20112 is opened in the main body of the single guide vane component 2011, and a guide vane cold air hole 20111 is opened on the main body of the single guide vane component 2011, and the guide vane cold air hole 20111 is connected to the cold air inlet cavity 20112;

[0076] A wall thermocouple wire measurement hole 20113 is also provided on the side surface of the main body of the single guide vane component 2011;

[0077] A cold air ring cavity baffle 20114 is installed at one end of the main body of the single guide vane component 2011.

[0078] Specifically, the guide vane outlet total pressure measuring rake 202 includes a cooling circulating water inlet pipe 2021, a cooling circulating water outlet pipe 2022, a total pressure measuring point 2023 and a total pressure test connecting pipe 2024. The cooling circulating water inlet pipe 2021 is connected to the cooling circulating water outlet pipe 2022 and flows through the circulating water to cool the area where the heat load of the guide vane outlet total pressure measuring rake 202 is concentrated. The total pressure measuring point 2023 cooperates with the total pressure test connecting pipe 2024 to measure the average total pressure of the incoming flow at multiple points; further, three groups of guide vane outlet total pressure measuring rakes are evenly spaced circumferentially. If necessary, the total pressure measuring rake can be connected to the flue gas analysis device to measure the gas components after combustion.

[0079] The use process of the present invention is as follows:

[0080] First, the igniter 111 is inserted into the flame tube 105 of the oblique injection annular flow interstage combustion chamber; the heated gas passes through the blunt body cooling gas pipe 104 and enters the flame tube 105 of the oblique injection annular flow interstage combustion chamber;

[0081] Secondly, the pressure measuring devices, temperature measuring devices and flue gas measuring devices in the interstage combustion chamber of the oblique injection circulation and the low-pressure turbine guide vane coupling test device are connected to the sensor interface to realize the real-time monitoring of various parameters in the combustion chamber test section 1 and the guide vane test section 2;

[0082] Then, the cooling air is passed into the bluff cooling air pipe 104 and the guide vane cooling air intake ring pipe 204 to reduce the impact of the local high heat load; the cooling water is passed into the support plate cooling water spray rod 206 and the cooling circulation water inlet pipe 2021 to protect the guide vane test section support plate 205 and the guide vane outlet total pressure measurement rake 202;

[0083] Finally, after waiting for the values ​​monitored by the incoming static pressure measuring tube 108, the incoming total pressure measuring tube 109 and the incoming temperature measuring thermocouple 110 to reach the set operating point, turn on the igniter 111 and immediately introduce fuel, and the fuel enters the oblique injection annular interstage combustion chamber flame tube 105 through the injection element 107; the user can observe the combustion start status downstream of the corresponding nozzle through the quartz glass observation window 103.

[0084] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0085] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A test device for coupling an interstage combustion chamber with oblique injection circulation and a low-pressure turbine guide vane, characterized in that: It comprises a combustion chamber test section (1) and a guide vane test section (2), wherein the guide vane test section (2) is fixedly connected to the inner and outer casings of the combustion chamber test section (1) via a flange and screws, and the other end of the guide vane test section (2) is fixedly connected to the exhaust section (3) via a flange and screws; The combustion chamber test section (1) comprises a bluff body inner casing (101), a diffuser outer casing (102), a quartz glass observation window (103) and a bluff body cooling air pipe (104); the bluff body inner casing (101) is fixedly connected to the inner wall of the diffuser outer casing (102); the leading edge bluff body of the bluff body inner casing (101) is open at one end close to the diffuser outer casing (102); the diffuser outer casing (102) is a profile structure; an oblique jet annular interstage combustion chamber flame tube (105) is installed between the opposite surfaces of the bluff body inner casing (101) and the diffuser outer casing (102); The quartz glass observation windows (103) are evenly distributed around the circumference and fixedly mounted on the diffuser outer casing (102); one end of the bluff body cooling air pipe (104) extends into the bluff body inner casing (101); the middle of the bluff body cooling air pipe (104) is compressed and sealed with the side wall of the bluff body inner casing (101) through a graphite gasket; the other end of the bluff body cooling air pipe (104) is fixedly connected with the outer side wall of the diffuser outer casing (102) through a screw; A combustion chamber outlet measuring thermocouple (106) is installed on the flange of the diffuser outer casing (102) and the outer flange of the oblique injection annular flow interstage combustion chamber flame tube (105), and the combustion chamber outlet measuring thermocouple (106) is located downstream of the combustion chamber outlet of the oblique injection annular flow interstage combustion chamber flame tube (105); An oil spraying member (107) is fixedly mounted on the outer side wall of the diffuser outer casing (102) via a pressure plate and a copper gasket, and an oil spraying port of the oil spraying member (107) is located at the combustion chamber inlet of the oblique injection annular interstage combustion chamber flame tube (105).

2. The device for testing the coupling between an interstage combustion chamber and a low-pressure turbine guide vane of an oblique injection circulation according to claim 1, characterized in that: It also includes an incoming static pressure measuring tube (108), an incoming total pressure measuring tube (109), an incoming temperature measuring thermocouple (110) and an igniter (111); the incoming static pressure measuring tube (108) is welded to the side wall of the diffuser outer casing (102); the incoming total pressure measuring tube (109) is fixedly connected to the diffuser outer casing (102) through a copper gasket and screws; the incoming temperature measuring thermocouple (110) is sealed and connected to the side wall of the diffuser outer casing (102); the igniter (111) passes through the diffuser outer casing (102) and the oblique injection annular flow interstage combustion chamber flame tube (105), and the ignition end of the igniter (111) extends into the oblique injection annular flow interstage combustion chamber flame tube (105).

3. The interstage combustion chamber and low-pressure turbine guide vane coupling test device of oblique injection circulation according to claim 1 is characterized by: The guide vane test section (2) comprises a guide vane disc assembly (201), a guide vane outlet total pressure measurement rake (202), a guide vane outlet temperature measurement thermocouple (203), a guide vane cooling air intake ring pipe (204), a guide vane test section support plate (205) and a support plate cooling water spray rod, and the guide vane disc assembly (201) is engaged and connected with the inner tube of the guide vane test section (2) through a boss clamping tooth; The guide vane outlet total pressure measuring rake (202) is sealedly connected to the outer tube of the guide vane test section (2) through a copper gasket and a screw, and one end of the guide vane outlet total pressure measuring rake (202) abuts against the outer side wall of the inner tube of the guide vane test section (2); The guide vane outlet temperature measuring thermocouple (203) passes through the outer tube of the guide vane test section (2) and abuts against the outer side wall of the inner tube of the guide vane test section (2); The guide vane cooling air intake ring pipe (204) is installed on the outside of the outer pipe of the guide vane test section (2), and the guide vane cooling air intake ring pipe (204) passes through the outer pipe of the guide vane test section (2) and is connected to the guide vane disc assembly (201); The guide vane test section support plate (205) is fixedly mounted between the outer tube of the guide vane test section (2) and the opposite surface of the inner tube of the guide vane test section (2), and the cross section of the guide vane test section support plate (205) is in the shape of a water drop; The support plate cooling water spray rod (206) passes through the outer tube of the guide vane test section (2), and the support plate cooling water spray rod (206) is located upstream of the guide vane test section support plate (205). The support plate cooling water spray rod (206) sprays water on a circumferential cross section to cool the guide vane test section support plate (205).

4. The test device for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection circulation according to claim 2 is characterized in that: The tail gas section (3) comprises a cooling cone (301) and an outer casing (302) of the tail gas section. The cooling cone (301) is evenly provided with cooling holes in a circumferential direction. The cooling holes are connected to the bluff cooling air pipe (104). The cooling cone (301) is fixedly connected to the inner tube of the guide vane test section (2) by means of screws. The cross section formed by the profile of the tail gas section outer casing (302) and the profile of the cold air cone (301) gradually increases, and the tail gas section outer casing (302) is fixedly connected to the outer tube of the guide vane test section (2) by means of screws.

5. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test device according to claim 1, characterized in that: The oblique-injection annular interstage combustion chamber flame tube (105) comprises a nozzle protection sleeve (1051), a wall oblique hole (1052), a front mixing hole (1053), a middle mixing hole (1054), and a rear mixing hole (1055); the axis of the nozzle protection sleeve (1051) forms a certain angle with the radial direction of the plane where it is located, and air film cooling holes are uniformly opened circumferentially on the side wall surface of the nozzle protection sleeve (1051); The wall inclined holes (1052) are all at certain angles to the radial direction and the axial direction, so as to prevent the airflow in the oblique injection annular flow interstage combustion chamber flame tube (105) from flowing circumferentially; The front section mixing hole (1053) is located downstream of the main combustion zone of the oblique injection annular flow interstage combustion chamber flame tube (105); The middle mixing hole (1054) is located in the middle of the nozzle protection cover (1051); the rear mixing hole (1055) is located at the bottom of the nozzle protection cover (1051), and the rear mixing hole (1055) is designed with an air duct structure.

6. The interstage combustion chamber and low-pressure turbine guide vane coupling test device of oblique injection circulation according to claim 3 is characterized by: The guide vane disc assembly (201) comprises a single guide vane component (2011) and a guide vane base (2012); the single guide vane component (2011) is evenly embedded along the circumference of the guide vane base (2012) via a latching tooth structure.

7. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test device according to claim 6, characterized in that: A cold air inlet cavity (20112) is provided in the main body of the single guide vane component (2011), a guide vane cold air hole (20111) is provided on the main body of the single guide vane component (2011), and the guide vane cold air hole (20111) is in communication with the cold air inlet cavity (20112); A wall thermocouple wire measurement hole (20113) is also provided on the side surface of the main body of the single guide vane component (2011); A cold air ring cavity baffle (20114) is installed at one end of the main body of the single guide vane component (2011).

8. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test device according to claim 3 is characterized by: The guide vane outlet total pressure measuring rake (202) comprises a cooling circulating water inlet pipe (2021), a cooling circulating water outlet pipe (2022), a total pressure measuring point (2023) and a total pressure test connecting pipe (2024); the cooling circulating water inlet pipe (2021) is connected to the cooling circulating water outlet pipe (2022); the total pressure measuring point (2023) and the total pressure test connecting pipe (2024) cooperate to measure the total pressure averaged at multiple points of the incoming flow.

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