Inclined jet circulation interstage combustion chamber and low-pressure turbine guide vane coupling test system

Abstract

The invention discloses an inclined jet circulation interstage combustion chamber and low-pressure turbine guide vane coupling test system, and relates to the technical field of aero-engine experiment devices, the inclined jet circulation interstage combustion chamber and low-pressure turbine guide vane coupling test system comprises a combustion chamber test section and a guide vane test section, and inner and outer casings of the guide vane test section and the combustion chamber test section are fixedly connected through flanges and screws; the other end of the guide vane test section is fixedly connected with the tail gas section through a flange and a screw. According to the oblique-spraying circulation interstage combustion chamber and low-pressure turbine guide vane coupling test system, the oil spraying piece extends into the flame tube at a certain angle to supply oil, and the inclined holes are formed in all parts of the flame tube to supply air, so that the residence time of fuel in the combustion chamber is prolonged, the combustion efficiency is improved, and the design concept of the interstage combustion chamber of pneumatic organization is realized; and a temperature sensor, a pressure sensor and a flue gas analysis device are arranged for data collection, and the method has important significance for analyzing related performance indexes of coupling of the oblique-spraying circulation interstage combustion chamber and the low-pressure turbine guide vane.

Description

[0001] This application is a divisional application. The application number of the original application is 202510045242.0, the application date is January 13, 2025, and the name of the invention is "A test device for coupling an interstage combustion chamber with oblique injection circulation and a low-pressure turbine guide vane". Technical Field

[0002] The invention relates to the technical field of aero-engine experimental devices, in particular to a coupling test system for an interstage combustion chamber and a low-pressure turbine guide vane with oblique injection and annular flow. Background Art

[0003] The current design goals for advanced aircraft engines / gas turbines in the world mainly focus on high compression ratio, high turbine inlet temperature, high thrust-to-weight ratio, low fuel consumption, high reliability and long life. According to the Brayton cycle principle, increasing the turbine inlet temperature and the engine's total compression ratio can effectively improve the engine's performance. The current compressor total pressure ratio and turbine inlet temperature have increased significantly compared to the 1960s. However, the engine turbine inlet total temperature is limited by the high-temperature resistance of the turbine material and cannot be significantly increased. In order to achieve supersonic flight, the mainstream improvement plan is to add an afterburner to the aircraft engine to increase the engine's thrust.

[0004] 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, that is, fuel economy, and the afterburner has more serious infrared radiation, which is not conducive to the aircraft's stealth.

[0005] An ideal cycle analysis of an aircraft engine equipped with an interstage combustion chamber shows that the installation of an interstage combustion chamber can increase the engine's unit thrust and reduce the engine's size while keeping the existing compressor total pressure ratio, turbine inlet total temperature, and fuel consumption rate approximately unchanged.

[0006] Without changing the existing compressor total pressure ratio or turbine inlet total temperature, and while maintaining the same fuel consumption, the interstage combustor can improve the engine's specific thrust and thermal efficiency, meeting aircraft engine requirements. Furthermore, while maintaining the original thrust, the temperature of the main combustion chamber can be lowered, thereby reducing NOx emissions and reducing pollution. This means that the interstage combustor is not limited by the total temperature in front of the turbine and has low infrared radiation. This allows it to meet stealth and manufacturing requirements while improving engine performance, thus offering broad prospects and advantages.

[0007] The high velocity and limited space within the turbine transition section, where the interstage combustor is located, make combustion difficult. Furthermore, research into the effects of interstage combustion on the low-pressure turbine guide vanes after adding an interstage combustor between the high- and low-pressure turbines remains limited. Therefore, there is an urgent need to design a test device for coupling an interstage combustor with low-pressure turbine guide vanes, utilizing circumferential circulation technology to increase the flame dwell time within a limited space and achieve more complete combustion. Furthermore, focusing on the matching patterns between interstage combustion and turbine guide vanes, and conducting relevant performance tests of the interstage combustion and low-pressure turbine coupling, has become a pressing issue for those skilled in the art. Summary of the Invention

[0008] The purpose of the present invention is to provide a test system 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.

[0009] In order to solve the above technical problems, the present invention adopts the following technical solutions: The present invention provides an oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system, 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 includes 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 profiled structure; an oblique jet annular flow interstage combustion chamber flame tube is installed between the opposing surfaces of the bluff body inner casing and the diffuser outer casing; 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 portion of the bluff body cooling air pipe is pressed and sealed with the side wall of the bluff body inner casing via 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 via a screw. 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; An oil spraying member is fixedly mounted on the outer side wall of the diffuser outer casing through a pressure plate and a copper gasket, and an oil spraying port of the oil spraying member is located at the combustion chamber inlet of the oblique injection annular flow interstage combustion chamber flame tube.

[0011] 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 through 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.

[0012] 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 with the inner tube of the guide vane test section through boss latches; The guide vane outlet total pressure measuring rake is sealedly 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; 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; The guide vane cooling air intake ring pipe is installed on the outside 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; The guide vane test section support plate is fixedly installed between the outer tube of the guide vane test section and the opposite surfaces 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; 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.

[0013] Preferably, the exhaust section includes a cooling cone and an exhaust section outer casing, the cooling cone is circumferentially uniformly provided with cooling holes, the cooling holes are connected to the bluff body cooling air pipe, and the cooling cone is fixedly connected to the inner tube of the guide vane test section by screws; 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.

[0014] Preferably, the oblique injection annular flow interstage combustion chamber flame tube includes 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 on which it is located, and air film cooling holes are uniformly opened circumferentially on the side wall surface of the nozzle protection sleeve. 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; 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; The middle mixing hole is located in the middle of the nozzle protection sleeve; the rear mixing hole is located at the bottom of the nozzle protection sleeve, and the rear mixing hole is designed with an air bleed pipe structure.

[0015] Preferably, the guide vane disc assembly includes 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 tooth structure.

[0016] 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; A wall thermocouple wire measurement hole is also provided on the side surface of the main body of the single guide vane component; A cold air ring cavity baffle is installed at one end of the main body of the single guide vane component.

[0017] 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.

[0018] Compared with the prior art, the present invention has the following beneficial technical effects: 1) Cooling air inlet holes are evenly distributed on the wall of the combustion chamber flame tube, which are set at a certain angle to the axial direction and the radial direction. While providing air intake to the combustion chamber, they also provide circumferential kinetic energy and extend the gas residence time, which can greatly improve combustion efficiency in the compact space of the interstage combustion chamber.

[0019] 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.

[0020] 3) The interaction between the front-end mixing holes in the combustion chamber flame tube creates a low-velocity recirculation zone on the axial cross-section, which is beneficial to flame stability. The rear-end mixing holes extend into the flame tube in the form of air bleed pipes, enhancing the penetration depth of the mixed gas and making the outlet temperature field more uniform.

[0021] 4) The interstage combustor is directly coupled to the low-pressure turbine guide vanes, enabling coupled hot testing. Measurements of combustor outlet temperature and pressure, low-pressure turbine guide vane outlet temperature and pressure, combustor outlet flue gas composition, and low-pressure turbine guide vane wall temperature are all possible. This allows for combustion performance testing of the interstage combustor and low-pressure turbine guide vanes.

[0022] 5) The design of the interstage combustion chamber casing of the oblique injection annular flow integrates the diffuser and the air inlet section, saving space and reducing pressure loss, which is of great significance for achieving a high-efficiency and low-resistance interstage combustion chamber design. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The present invention will be further described below with reference to the accompanying drawings.

[0024] Figure 1 This is a half-section view of a test system for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection annular flow according to the present invention; Figure 2 This is a schematic diagram of the overall structure of a test system for coupling an interstage combustion chamber and a low-pressure turbine guide vane with oblique injection and annular flow according to the present invention; Figure 3 is a half-section view of a combustion chamber test section of the present invention; Figure 4 This is an overall structural view of the combustion chamber test section of the present invention; Figure 5 Schematic diagram of the arrangement of the combustion chamber outlet temperature and total pressure measuring points of the combustion chamber test section of the present invention; Figure 6 It is a schematic diagram of the installation position of the combustion chamber fuel system and the igniter of the present invention; Figure 7 Schematic diagram of the oblique-injection annular flow interstage combustion chamber flame tube of the combustion chamber test section of the present invention; Figure 8 is a partial cross-sectional view of the guide vane test section of the present invention; Figure 9 is a half-section view of a guide vane test section of the present invention; Figure 10 is an overall view of the guide vane plate assembly of the present invention; Figure 11 is a general detail view of a single component of a guide vane of the present invention; Figure 12 is a half-section view of a guide vane outlet total pressure measuring rake of the present invention; Figure 13 It is a half-section view of the tail gas section of the present invention.

[0025] Explanation of Reference Numerals: 1. Combustion chamber test section; 101. Blunt body inner casing; 102. Diffuser outer casing; 103. Quartz glass observation window; 104. Blunt body cooling air duct; 105. Oblique jet annular interstage combustion chamber flame tube; 106. Combustion chamber outlet measurement thermocouple; 107. Fuel injection element; 108. Inlet static pressure measuring tube; 109. Inlet total pressure measuring tube; 110. Inlet temperature measuring thermocouple; 111. Ignitor; 1051. Nozzle protection sleeve; 1052. Wall inclined hole; 1053. Front section mixing hole; 1054. Middle section mixing hole; 1055. Rear section mixing hole; 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 inlet 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 cooling air hole; 20112. Cooling air inlet cavity; 20113. Wall thermocouple wire measurement hole; 20114. Cooling air ring cavity baffle; 3. Exhaust section; 301. Cooling cone; 302. Exhaust section outer casing. DETAILED DESCRIPTION

[0026] 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 with reference to 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 intended to limit the present invention.

[0027] like Figure 1-13 As shown, a test system for coupling an interstage combustion chamber and a low-pressure turbine guide vane with an oblique injection annular flow 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 through flanges and screws, and the other end of the guide vane test section 2 is fixedly connected to the exhaust section 3 through flanges and screws.

[0028] like Figure 3-4As 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 duct 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, which makes it difficult for the airflow to separate during the flow and allows the incoming flow to be diffused, thereby reducing the total pressure loss of the combustion chamber. An oblique injection annular flow interstage combustion chamber flame tube 105 is installed between the opposing 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. Five quartz glass observation windows 103 are evenly distributed around the circumference. One end of the bluff body cooling air pipe 104 extends into the bluff body inner casing 101. The middle portion of the bluff body cooling air pipe 104 is tightly sealed to the side wall of the bluff body inner casing 101 via a graphite gasket. The other end of the bluff body cooling air pipe 104 is fastened to the outer wall of the diffuser outer casing 102 via screws. Combustion chamber outlet measuring thermocouples 106 are 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 thermocouples 106 are located downstream of the combustion chamber outlet of the oblique injection annular flow interstage combustion chamber flame tube 105. The combustion chamber outlet measuring thermocouples 106 are arranged in two of the five circumferential periods of 72°, and in one period, three thermocouples are distributed at intervals of 25°, with their starting positions being 11° apart from the 72° period boundary, and in one period, four thermocouples are distributed at intervals of 24°, with their starting positions being at the 72° period boundary. An oil spray piece 107 is fixedly installed on the outer wall of the diffuser outer casing 102 through a pressure plate and a copper gasket, and the oil injection port of the oil spray piece 107 is located at the combustion chamber inlet of the oblique injection annular interstage combustion chamber flame tube 105. There are five oil spray pieces 107 evenly arranged around the circumference, and the nozzle direction forms an angle of 45° with the radial direction of the cross section.

[0029] 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 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.

[0030] 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 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 with the inner tube of the guide vane test section 2 through boss teeth to prevent rotation due to circumferential force. 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 screws, 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 to provide cooling air for the guide vane disc assembly 201; 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 teardrop shape; 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 the guide vane test section support plate 205.

[0031] Specifically, the exhaust section 3 includes a cooling cone 301 and an exhaust section outer casing 302. The cooling cone 301 is evenly circumferentially provided with cooling holes, which are connected to the bluff body cooling air pipe 104 and discharge the air introduced by the bluff body cooling air pipe 104. The cooling cone 301 is fixedly connected to the inner tube of the guide vane test section 2 by screws. 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 decelerating the exhaust pressure. The exhaust section outer casing 302 is fixedly connected to the outer tube of the guide vane test section 2 by screws.

[0032] Specifically, the oblique-injection annular 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 a 45° angle with the radial direction of the plane in which it is located. Air film cooling holes with a diameter of 0.5 mm are uniformly opened circumferentially on the side wall surface, and an oil outlet hole and a swirl sweeper are provided on the head. 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; The front section mixing hole 1053 is located downstream of the main combustion zone of the oblique injection annular interstage combustion chamber flame tube 105 and is used for air supplement and mixing; The middle mixing hole 1054 is located in the middle of the nozzle protective sleeve 1051 and is used to mix the cooling gas; the rear mixing hole 1055 is located at the bottom of the nozzle protective sleeve 1051, and the rear mixing hole 1055 is designed with an air bleed pipe structure, which allows the mixed gas to penetrate deeper and make the outlet temperature field more uniform.

[0033] 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 along the circumference through a latching structure. Furthermore, 30 single guide vane components are evenly distributed along the circumference.

[0034] 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; 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.

[0035] Specifically, the guide vane outlet total pressure measurement rake 202 includes a cooling water inlet pipe 2021, a cooling water outlet pipe 2022, a total pressure measurement point 2023, and a total pressure test connection pipe 2024. The cooling water inlet pipe 2021 is connected to the cooling water outlet pipe 2022, and circulating water flows through it, cooling the area of ​​the guide vane outlet total pressure measurement rake 202 where the heat load is concentrated. The total pressure measurement point 2023 cooperates with the total pressure test connection pipe 2024 to measure the average total pressure of the incoming flow at multiple points. Furthermore, three groups of guide vane outlet total pressure measurement rakes are evenly spaced circumferentially. If necessary, the total pressure measurement rake can be connected to a flue gas analyzer to measure post-combustion gas components.

[0036] The use process of the present invention is as follows: 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; Secondly, the pressure, temperature, and flue gas measurement devices in the oblique-injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test device were connected to the sensor interface to achieve real-time monitoring of various parameters in the combustion chamber test section 1 and the guide vane test section 2. Then, cooling air is passed into the bluff body cooling air pipe 104 and the guide vane cooling air inlet ring pipe 204 to reduce the impact of local high heat load; cooling water is passed into the support plate cooling water spray rod 206 and the cooling circulating water inlet pipe 2021 to protect the guide vane test section support plate 205 and the guide vane outlet total pressure measurement rake 202; 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, the igniter 111 is turned on and fuel is immediately introduced. The fuel enters the flame tube 105 of the oblique injection annular interstage combustion chamber through the injection element 107; the user can observe the combustion start-up status downstream of the corresponding nozzle through the quartz glass observation window 103.

[0037] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0038] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A test system for coupling an interstage combustion chamber with oblique injection and annular flow and a low-pressure turbine guide vane, characterized by: 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 flanges and screws, and the other end of the guide vane test section (2) is fixedly connected to the exhaust section (3) via flanges 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 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); The quartz glass observation window (103) is evenly distributed around the circumference and is 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 portion of the bluff body cooling air pipe (104) is compressed and sealed with the side wall of the bluff body inner casing (101) via a graphite gasket; the other end of the bluff body cooling air pipe (104) is fixedly connected to the outer side wall of the diffuser outer casing (102) via 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); 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), wherein 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 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); The oblique injection annular flow interstage combustion chamber flame tube (105) comprises a nozzle protection sleeve (1051), a wall oblique hole (1052), a front section mixing hole (1053), a middle section mixing hole (1054), and a rear section 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 on the side wall surface of the nozzle protection sleeve (1051) in a circumferential direction; 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 sleeve (1051); the rear mixing hole (1055) is located at the bottom of the nozzle protection sleeve (1051), and the rear mixing hole (1055) is designed with an air duct structure.

2. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system according to claim 1, characterized in that: 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; the guide vane disc assembly (201) is engaged with the inner tube of the guide vane test section (2) via boss latches; 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 in communication with 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 surfaces 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).

3. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system according to claim 1, 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 pipe of the guide vane test section (2) by 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 screws.

4. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system according to claim 2, characterized in that: 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.

5. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system according to claim 4, 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).

6. The oblique injection annular flow interstage combustion chamber and low-pressure turbine guide vane coupling test system according to claim 2, characterized in that: The guide vane outlet total pressure measuring rake (202) comprises a cooling circulation water inlet pipe (2021), a cooling circulation water outlet pipe (2022), a total pressure measuring point (2023) and a total pressure test connecting pipe (2024); the cooling circulation water inlet pipe (2021) is connected to the cooling circulation water outlet pipe (2022); the total pressure measuring point (2023) cooperates with the total pressure test connecting pipe (2024) to measure the total pressure averaged at multiple points of the incoming flow.

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