Experiment piece and experiment structure for researching influence of labyrinth seal air entraining jet flow structure on performance of gas compressor

Abstract

The utility model discloses an experiment piece and an experiment structure for studying the influence of a labyrinth seal air-entraining jet flow structure on the performance of a gas compressor, the experiment piece can form an annular pressure-equalizing cavity through the cooperation of the labyrinth seal structure and a shrouded stationary blade, and the annular pressure-equalizing cavity is used for transitioning injected gas flow and playing a role in pressure-equalizing jet flow. In addition, the annular pressure equalizing cavity can improve the adaptability of the static blades and the labyrinth sealing structure, the problem that the static blades are matched with the jet holes in the sealing lining in a one-to-one correspondence mode does not need to be considered, the influence caused by on-way resistance loss of the jet holes can be eliminated when the effects of different jet outlets are tested, and the testing accuracy is improved. Finally, convenient and low-cost test research can be realized under the condition that various test pieces are combined, the test structure adopts the test pieces to test the test pieces with different air-entraining jet structures, and the influence of different labyrinth seal air-entraining jet structures on the performance of the gas compressor can be known.

Description

Technical Field

[0001] The utility model relates to an experimental structure, in particular to an experimental piece and an experimental structure for studying the influence of a comb tooth sealing bleed air jet structure on compressor performance. Background Art

[0002] As an integral part of the aviation, aerospace and marine industries, the working environment of the compressor has become increasingly harsh with the continuous development of the engine, which has put forward new requirements for the performance of the compressor. As an important component of an aircraft engine, the performance of the compressor significantly affects the efficiency and stability margin of the whole machine. Studies have shown that the leakage between the compressor stages will deteriorate the internal flow field structure of the compressor, deteriorate the flow capacity of the compressor, reduce the efficiency, and be accompanied by the occurrence of compressor surge. Comb seals, as a sealing structure to reduce leakage between the moving and stationary blades of the compressor, have been widely used in aircraft engines. They can reduce the leakage flow between the compressor stages and improve the performance of the compressor. However, the gaps in the comb teeth sealing structure will still lead to the generation of leakage flow, which will damage the flow field structure. In order to suppress the damage of the leakage flow to the flow field structure, an air bleed jet structure is designed in the prior art (disclosed in CN 117605712 A), the purpose of which is to move the angular zone separation of the stator blades axially backward and reduce the angular zone separation range, thereby improving the compressor performance. However, how to simply and conveniently obtain relevant data on the influence of different air bleed jet structures on the compressor performance through experimental pieces and experimental systems has become a problem to be solved urgently. Utility Model Content

[0003] In view of this, the purpose of the utility model is to provide an experimental piece and an experimental system for studying the influence of the comb seal bleed air jet structure on the compressor performance, so as to solve the problem in the prior art that relevant data on the influence of different bleed air jet structures on the compressor performance cannot be obtained.

[0004] On the one hand, the utility model provides an experimental piece for studying the influence of a comb-tooth sealing bleed air jet structure on compressor performance, comprising: a comb-tooth sealing structure and a crowned stationary blade, wherein the comb-tooth sealing structure comprises a sealing bushing and a comb-tooth sealing body, the crowned stationary blade is multiple and is slidably connected to the sealing bushing in sequence, an annular pressure equalizing chamber is formed between the sealing bushing and the crowned stationary blade connected to its outer periphery, a jet outlet connected to the annular pressure equalizing chamber is provided at the bottom of a suction surface of part or all of the crowned stationary blades, the sealing bushing is provided with bleed air inlets connected to the annular pressure equalizing chamber at equal intervals along its circumference, the comb-tooth sealing body is clearance-matched with the sealing bushing to form a compressor interstage comb-tooth sealing structure.

[0005] Preferably, the shrouded stationary blade is slidably connected to the sealing bushing via a dovetail groove structure.

[0006] Further preferably, the height of the annular pressure equalizing chamber is 0.6 to 0.8 times the height of the sealing bushing, and the width of the annular pressure equalizing chamber = 1.2*the projection distance from the bleed air inlet to the jet outlet along the axial direction of the sealing bushing.

[0007] The utility model also provides an experimental structure for studying the influence of the comb-teeth sealing bleed air jet structure on the performance of the compressor, comprising: a stator casing, a moving blade casing, a rotor, a crowned stator blade, a moving blade, a comb-teeth sealing structure, a pressure detection unit and a temperature detection unit, wherein the comb-teeth sealing structure comprises a sealing bushing and a comb-teeth sealing body, the stator casing and the moving blade casing are cooperatively installed on the outside of the rotor, the moving blade is fixedly installed on the outer peripheral surface of the rotor, the crowned stator blade is multiple and is slidably connected to the inner periphery of the stator casing in sequence, the sealing bushing is slidably connected to the other end of the crowned stator blade in sequence and forms an annular pressure equalizing chamber with the crowned stator blade, and the bottom of the suction surface of some or all of the crowned stator blades is provided with a jet outlet connected to the annular pressure equalizing chamber. The sealing bushing is provided with air inlets connected with the annular pressure equalizing chamber at equal intervals along its circumference, an annular cavity is provided on the outer circumference of the rotor, the comb tooth sealing body is installed in the annular cavity, the sealing bushing is clearance-matched with the comb tooth sealing body and the two sides respectively form a cavity inlet and a cavity outlet with the wall surface of the annular cavity, the pressure detection unit comprises a comb tooth sealing inlet total pressure probe, a comb tooth sealing inlet static pressure probe, a comb tooth sealing outlet static pressure probe, an annular pressure equalizing chamber static pressure probe, a moving blade front static pressure probe, a shrouded static blade leading edge static pressure probe, a shrouded static blade trailing edge static pressure probe, an experimental structure inlet total pressure probe, and a shrouded static blade outlet total pressure probe, and the temperature detection unit comprises an experimental structure inlet total temperature probe and a comb tooth sealing inlet total temperature probe.

[0008] Preferably, the stator casing, the moving blade casing and the rotor are all separately assembled structures.

[0009] Further preferably, the stator casing, the moving blade casing and the rotor are divided into two symmetrical parts and connected by bolts, and the stator casing and the moving blade casing are connected by flanges and bolts.

[0010] Further preferably, the stator casing, the crowned stator blades and the sealing bushing are all connected via a slide groove structure, and the comb tooth sealing body and the annular cavity are connected via a slide groove structure.

[0011] It is further preferred that both sides of the sealing bushing are provided with a comb-teeth sealing inlet static pressure probe hole and a comb-teeth sealing outlet static pressure probe hole at intervals along its circumference, and the comb-teeth sealing inlet static pressure probe and the comb-teeth sealing outlet static pressure probe are installed in the comb-teeth sealing inlet static pressure probe hole and the comb-teeth sealing outlet static pressure probe hole respectively; the cavity inlet side of the sealing bushing is also provided with a comb-teeth sealing inlet total pressure probe hole and a comb-teeth sealing inlet total temperature probe hole at intervals, and the comb-teeth sealing inlet total pressure probe and the comb-teeth sealing inlet total temperature probe are installed in the comb-teeth sealing inlet total pressure probe hole and the comb-teeth sealing inlet total temperature probe hole respectively; the bottom of some of the crowned stationary blades is provided with an annular pressure equalizing chamber static pressure probe hole, and the annular pressure equalizing chamber static pressure probe is installed in the annular pressure equalizing chamber static pressure probe hole respectively; the moving blade casing is provided with a moving blade front static pressure probe hole, and the moving blade front static pressure probe hole is provided with a moving blade front static pressure probe hole. A pressure probe is installed in the static pressure probe hole in front of the moving blade. A static pressure probe hole at the leading edge of a crowned stator blade and a static pressure probe hole at the trailing edge of a crowned stator blade are arranged on the stator casing. The static pressure probe at the leading edge of the crowned stator blade and the static pressure probe at the trailing edge of the crowned stator blade are installed in the static pressure probe hole at the leading edge of the crowned stator blade and the static pressure probe at the trailing edge of the crowned stator blade respectively. An experimental structure inlet total pressure probe hole and an experimental structure inlet total temperature probe hole are also arranged on the moving blade casing. The experimental structure inlet total pressure probe and the experimental structure inlet total temperature probe are installed in the experimental structure inlet total pressure probe hole and the experimental structure inlet total temperature probe respectively. A five-hole pneumatic probe hole and a displacement mechanism thereof are arranged on the hub flange of the crowned stator blade outlet. The crowned stator blade outlet total pressure probe is installed in the five-hole pneumatic probe hole for detecting the aerodynamic parameters of the crowned stator blade outlet.

[0012] The experimental piece provided by the utility model for studying the influence of the comb tooth sealing air bleed jet structure on the compressor performance can transition the induced airflow through the setting of the annular pressure equalizing chamber, thereby achieving the effect of pressure equalizing jet and ensuring that the pressure corresponding to each jet outlet is consistent. In addition, the annular pressure equalizing chamber can improve the adaptability of the stationary blade and the comb tooth sealing structure, and there is no need to consider the one-to-one correspondence between the stationary blade and the jet holes on the sealing bushing. When testing the effects of different jet outlets, the influence of the resistance loss along the jet hole can also be eliminated, and finally convenient and low-cost experimental research can be achieved under the combination of various experimental pieces.

[0013] The utility model provides an experimental structure for studying the influence of a comb-teeth sealing bleed air jet structure on compressor performance. By replacing experimental pieces (comb-teeth sealing structures and / or crowned stator blades) with different bleed air jet structures, pressure and temperature data at different positions in the experimental structure under different combinations of comb-teeth sealing structures and crowned stator blades can be detected, and then the influence of different combinations of comb-teeth sealing structures and crowned stator blades on compressor performance can be obtained through data analysis, wherein changes to the bleed air jet structure include but are not limited to the following changes: changing the position, angle, size, etc. of the bleed air inlet and the jet outlet; changing the height and width of the annular pressure equalizing chamber, etc. An annular pressure equalizing chamber is formed between the sealing sleeve of the comb tooth sealing structure being tested and the crowned stator blade, which is used for the transitional induced airflow and can achieve the effect of pressure equalizing jet, ensuring that the pressure corresponding to each jet outlet is consistent. In addition, due to the existence of the annular pressure equalizing chamber, when it is necessary to replace the crowned stator blade and the comb tooth sealing structure, there is no need to consider the one-to-one correspondence between the crowned stator blade and the jet holes on the sealing sleeve. When testing the effects of different jet outlets, the influence of the resistance loss along the jet hole can also be eliminated. Ultimately, convenient and low-cost experimental research can be achieved under the condition of a variety of experimental parts combinations, thereby understanding the influence of different comb tooth sealing induced air jet structures on the compressor performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention is further described in detail below in conjunction with the accompanying drawings and implementation methods:

[0015] Figure 1 A schematic diagram of the connection between the grate seal structure and a single shrouded stationary blade in an experimental piece provided by the utility model for studying the influence of the grate seal bleed air jet structure on the compressor performance;

[0016] Figure 2 A cross-sectional view of the cooperation between the experimental piece and the rotor provided by the utility model for studying the influence of the comb teeth sealing bleed air jet structure on the compressor performance;

[0017] Figure 3 A three-dimensional diagram of an experimental structure provided by the utility model for studying the influence of the comb teeth sealing bleed air jet structure on the compressor performance;

[0018] Figure 4 The utility model provides a cross-sectional view of an experimental structure for studying the influence of the comb teeth sealing bleed air jet structure on the compressor performance. DETAILED DESCRIPTION

[0019] The present invention will be further explained below in conjunction with specific implementation schemes, but the present invention is not limited thereto.

[0020] In order to test the influence of different bleed air jet structures on compressor performance, such as Figure 1 , Figure 2 , Figure 4As shown, on the one hand, the utility model provides an experimental piece for studying the influence of the comb-tooth sealing bleed air jet structure on the compressor performance, comprising: a comb-tooth sealing structure and a crowned stationary blade 4, wherein the comb-tooth sealing structure comprises a sealing bushing 7 and a comb-tooth sealing body 8, the crowned stationary blade 4 is multiple and is slidably connected to the sealing bushing 7 in sequence, an annular pressure equalizing chamber 71 is formed between the sealing bushing 7 and the crowned stationary blade 4 connected to its outer periphery, a jet outlet 41 connected to the annular pressure equalizing chamber 71 is provided at the bottom of the suction surface of part or all of the crowned stationary blades 4, the sealing bushing 7 is provided with bleed air inlets 72 connected to the annular pressure equalizing chamber 71 at equal intervals along its circumference, the comb-tooth sealing body 8 is clearance-matched with the sealing bushing 7 to form a compressor inter-stage comb-tooth sealing structure.

[0021] The experimental piece used to study the influence of the comb-teeth sealing bleed air jet structure on the compressor performance can transition the induced airflow through the setting of the annular pressure equalizing chamber, play the effect of pressure equalizing jet, and ensure that the pressure corresponding to each jet outlet is consistent. In addition, the annular pressure equalizing chamber can improve the adaptability of the stationary blade and the comb-teeth sealing structure, and there is no need to consider the one-to-one correspondence between the stationary blade and the jet holes on the sealing bushing. When testing the effects of different jet outlets, the influence of the resistance loss along the jet hole can also be eliminated. Finally, convenient and low-cost experimental research can be achieved under the combination of various experimental pieces.

[0022] As an improvement of the technical solution, the shrouded stationary blade 4 is slidably connected to the sealing bushing 7 via a dovetail groove structure.

[0023] In order to avoid the increase of flow resistance in the jet process and the influence of jet effect due to the large cross-section of the annular pressure equalizing chamber, as an improvement of the technical solution, the height of the annular pressure equalizing chamber 71 is 0.6 to 0.8 times the height of the sealing bushing 7, and the width of the annular pressure equalizing chamber 71 = 1.2*the projection distance from the air inlet 72 to the jet outlet 41 along the axial direction of the sealing bushing 7.

[0024] like Figure 3 , Figure 4As shown, the utility model also provides an experimental structure for studying the influence of the grate-teeth sealing bleed air jet structure on the performance of the compressor, comprising: a stator casing 1, a moving blade casing 2, a rotor 3, a crowned stator blade 4, a moving blade 5, a grate-teeth sealing structure, a pressure detection unit (not shown in the figure) and a temperature detection unit (not shown in the figure), wherein the grate-teeth sealing structure comprises a sealing bushing 7 and a grate-teeth sealing body 8, the stator casing 1 and the moving blade casing 2 are cooperatively installed on the outside of the rotor 3, the moving blade 5 is fixedly installed on the outer peripheral surface of the rotor 3, the crowned stator blade 4 is multiple and is slidably connected to the inner periphery of the stator casing 1 in sequence, the sealing bushing 7 is slidably connected to the other end of the crowned stator blade 4 in sequence and forms an annular pressure equalizing cavity 71 between the crowned stator blade 4, and the bottom of the suction surface of part or all of the crowned stator blades 4 is provided with a pressure equalizing cavity connected to the annular pressure equalizing cavity The jet outlet 41 is connected to the annular pressure equalizing chamber 71, the sealing bushing 7 is provided with air inlets 72 connected to the annular pressure equalizing chamber 71 at equal intervals along its circumference, an annular cavity 31 is provided on the outer circumference of the rotor 3, the comb tooth sealing body 8 is installed in the annular cavity 31, the sealing bushing 7 is clearance-matched with the comb tooth sealing body 8, and the two sides respectively form a cavity inlet 311 and a cavity outlet 312 with the wall surface of the annular cavity 31, the pressure detection unit comprises a comb tooth sealing inlet total pressure probe, a comb tooth sealing inlet static pressure probe, a comb tooth sealing outlet static pressure probe, an annular pressure equalizing chamber static pressure probe, a moving blade front static pressure probe, a shrouded static blade leading edge static pressure probe, a shrouded static blade trailing edge static pressure probe, an experimental structure inlet total pressure probe, and a shrouded static blade outlet total pressure probe, and the temperature detection unit comprises an experimental structure inlet total temperature probe and a comb tooth sealing inlet total temperature probe.

[0025] The experimental structure used to study the influence of the comb-teeth sealing bleed air jet structure on the compressor performance can detect the pressure and temperature data of different positions in the experimental structure under different combinations of the comb-teeth sealing structure and the shrouded stator blades by replacing the comb-teeth sealing structure and / or the shrouded stator blades, and then obtain the influence of different combinations of the comb-teeth sealing structure and the shrouded stator blades on the compressor performance through data analysis, wherein the purpose of replacing the comb-teeth sealing structure and the shrouded stator blades is to change the bleed air jet structure, including but not limited to the following changes: changing the position, angle, size, etc. of the bleed air inlet and the jet outlet; changing the annular pressure equalizing The height and width of the cavity, etc., wherein an annular pressure equalizing cavity is formed between the sealing bushing of the comb tooth sealing structure being tested and the crowned stator blade, which is used for the transitional airflow to achieve the effect of pressure equalizing jet and ensure that the pressure corresponding to each jet outlet is consistent. In addition, due to the existence of the annular pressure equalizing cavity, when it is necessary to replace the crowned stator blade and the comb tooth sealing structure, there is no need to consider the one-to-one correspondence between the crowned stator blade and the jet holes on the sealing bushing. When testing the effects of different jet outlets, the influence of the resistance loss along the jet hole can also be eliminated. Ultimately, convenient and low-cost experimental research can be achieved under the condition of multiple experimental parts combinations.

[0026] In order to facilitate the assembly of the experimental structure, as an improvement of the technical solution, the stator casing 1, the moving blade casing 2, and the rotor 3 are all split assembly structures. Preferably, the stator casing 1, the moving blade casing 2, and the rotor 3 are divided into two symmetrical parts and connected by bolts, and the stator casing and the moving blade casing are connected by flanges and bolts.

[0027] In order to facilitate the replacement and installation of the tested comb teeth sealing structure and / or crowned stator blades and reduce the experimental cost and experimental cycle, as an improvement of the technical solution, the stator casing 1, the crowned stator blades 4, and the sealing bushing 7 are connected by a slide groove structure, and the comb teeth sealing body 8 is connected to the annular cavity 31 by a slide groove structure.

[0028] As an improvement of the technical solution, both sides of the sealing bushing 7 are provided with a comb-teeth-seal inlet static pressure probe hole and a comb-teeth-seal outlet static pressure probe hole at intervals along its circumference, and the comb-teeth-seal inlet static pressure probe and the comb-teeth-seal outlet static pressure probe are installed in the comb-teeth-seal inlet static pressure probe hole and the comb-teeth-seal outlet static pressure probe hole respectively. Preferably, four of the comb-teeth-seal inlet static pressure probe holes and the comb-teeth-seal outlet static pressure probe holes are arranged at equal intervals along the circumference of the sealing bushing 7; the cavity inlet side of the sealing bushing 7 is also provided with a comb-teeth-seal inlet total pressure probe hole and a comb-teeth-seal inlet total temperature probe hole at intervals, and the comb-teeth-seal inlet total pressure probe and the comb-teeth-seal outlet static pressure probe are installed in the comb-teeth-seal inlet static pressure probe hole and the comb-teeth-seal outlet static pressure probe hole respectively. The strict inlet total temperature probe is correspondingly installed in the comb-teeth-sealed inlet total pressure probe hole and the comb-teeth-sealed inlet total temperature probe hole. Preferably, two of the comb-teeth-sealed inlet total pressure probe hole and two of the comb-teeth-sealed inlet total temperature probe holes are evenly spaced along the circumference of the sealing bushing 7; an annular pressure equalizing chamber static pressure probe hole is provided at the bottom of some of the crowned stator blades 4, and the annular pressure equalizing chamber static pressure probe is correspondingly installed in the annular pressure equalizing chamber static pressure probe hole. Preferably, four of the annular pressure equalizing chamber static pressure probe holes are evenly spaced along the circumference of the ring formed by the crowned stator blades 4; wherein the wires of each probe can be connected to an external power supply through a wire through hole provided on the crowned stator blades 4.

[0029] In order to obtain more flow field information, as an improvement of the technical solution, a static pressure detection hole in front of the moving blade is provided on the moving blade casing 2, and the static pressure probe in front of the moving blade is installed in the static pressure detection hole in front of the moving blade; a static pressure detection hole at the leading edge of the crowned static blade and a static pressure detection hole at the trailing edge of the crowned static blade are provided on the stator casing 1, and the static pressure probe at the leading edge of the crowned static blade and the static pressure probe at the trailing edge of the crowned static blade are correspondingly installed in the static pressure detection hole at the leading edge of the crowned static blade and the static pressure detection hole at the trailing edge of the crowned static blade; preferably, a plurality of the three static pressure detection holes are evenly distributed along the circumference of the casing; An experimental structure inlet total pressure probe hole and an experimental structure inlet total temperature probe hole are also provided on the moving blade casing 2, and the experimental structure inlet total pressure probe and the experimental structure inlet total temperature probe are respectively installed in the experimental structure inlet total pressure probe hole and the experimental structure inlet total temperature probe hole; five-hole pneumatic probe holes and their displacement mechanisms are provided on the hub flange of the crowned stationary blade outlet, and the crowned stationary blade outlet total pressure probe is installed in the five-hole pneumatic probe holes for detecting the aerodynamic parameters of the crowned stationary blade outlet.

[0030] The method for conducting an experiment using the above-mentioned experimental structure for studying the influence of the comb tooth sealing bleed air jet structure on the compressor performance is as follows: the bleed air jet structure is changed by replacing the comb tooth sealing structure and / or the crowned stator blades, and the pressure detection unit and the temperature detection unit are used to detect the pressure and temperature data at different positions in the experimental structure under different combinations of comb tooth sealing structures and crowned stator blades. After data analysis, the above data can be used to obtain the influence of different comb tooth sealing structures and crowned stator blade combination structures on the compressor performance, and then the influence of different bleed air jet structures on the compressor performance can be obtained, wherein changing the bleed air jet structure includes but is not limited to the following changes: changing the position, angle, size, etc. of the bleed air inlet and the jet outlet; changing the height and width of the annular pressure equalizing chamber, etc.

[0031] In which, the leakage amount of the grate seal structure can also be calculated by the data obtained from the experimental structure for studying the influence of the grate seal bleed air jet structure on the compressor performance, wherein the formula for calculating the leakage amount of the grate seal structure is as follows:

[0032]

[0033] In the formula, Q represents the leakage of the comb tooth sealing structure, and P1 are the total pressure at the grate seal inlet, the total temperature at the grate seal inlet, and the static pressure at the grate seal outlet, respectively. g and k are the gas constant and adiabatic index respectively. A is generally taken as the minimum flow area of ​​the tooth top of the interstage comb tooth sealing structure, A = 2π × R × c, where R is the rotor radius corresponding to the tooth top, and c is the gap between the tooth top and the sealing bushing.

[0034] The specific implementation methods of the present utility model are written in a progressive manner, emphasizing the differences between the various implementation methods, and the similar parts thereof can be referenced to each other.

[0035] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. An experimental piece for studying the influence of the comb seal bleed air jet structure on the compressor performance, characterized in that: include: A comb tooth sealing structure and a crowned stationary blade (4), wherein the comb tooth sealing structure comprises a sealing bushing (7) and a comb tooth sealing body (8), the crowned stationary blade (4) is multiple and is slidably connected to the sealing bushing (7) in sequence, an annular pressure equalizing chamber (71) is formed between the sealing bushing (7) and the crowned stationary blade (4) connected to its outer periphery, a jet outlet (41) communicating with the annular pressure equalizing chamber (71) is provided at the bottom of the suction surface of part or all of the crowned stationary blades (4), the sealing bushing (7) is provided with bleed air inlets (72) communicating with the annular pressure equalizing chamber (71) at equal intervals along its circumference, the comb tooth sealing body (8) is clearance-matched with the sealing bushing (7) to form a compressor interstage comb tooth sealing structure.

2. The experimental piece for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 1, characterized in that: The shrouded stationary blade (4) is slidably connected to the sealing bushing (7) via a dovetail groove structure.

3. The experimental piece for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 1, characterized in that: The height of the annular pressure equalizing chamber (71) is 0.6 to 0.8 times the height of the sealing bushing (7), and the width of the annular pressure equalizing chamber (71) is 1.2*the projection distance from the air inlet (72) to the jet outlet (41) along the axial direction of the sealing bushing (7).

4. An experimental structure for studying the influence of the comb seal bleed air jet structure on the compressor performance, characterized in that: include: A stator casing (1), a moving blade casing (2), a rotor (3), a crowned stator blade (4), a moving blade (5), a grate sealing structure, a pressure detection unit and a temperature detection unit, wherein the grate sealing structure comprises a sealing bushing (7) and a grate sealing body (8), the stator casing (1) and the moving blade casing (2) are cooperatively mounted on the outside of the rotor (3), the moving blade (5) is fixedly mounted on the outer peripheral surface of the rotor (3), the crowned stator blade (4) is a plurality of stator blades (4) which are slidably connected to the inner periphery of the stator casing (1) in sequence, the sealing bushing (7) is slidably connected to the other end of the crowned stator blade (4) in sequence and an annular pressure equalizing chamber (71) is formed between the sealing bushing (7) and the crowned stator blade (4), the bottom of the suction surface of some or all of the crowned stator blades (4) is provided with a jet outlet (41) which is connected to the annular pressure equalizing chamber (71), the sealing bushing (7 ) is provided with air inlets (72) connected to the annular pressure equalizing chamber (71) at equal intervals along its circumference, an annular cavity (31) is provided on the outer circumference of the rotor (3), the comb tooth seal body (8) is installed in the annular cavity (31), the sealing bushing (7) is clearance-matched with the comb tooth seal body (8) and the two sides respectively form a cavity inlet (311) and a cavity outlet (312) with the wall surface of the annular cavity (31), the pressure detection unit includes a comb tooth seal inlet total pressure probe, a comb tooth seal inlet static pressure probe, a comb tooth seal outlet static pressure probe, an annular pressure equalizing chamber static pressure probe, a moving blade front static pressure probe, a shrouded static blade leading edge static pressure probe, a shrouded static blade trailing edge static pressure probe, an experimental structure inlet total pressure probe, and a shrouded static blade outlet total pressure probe, and the temperature detection unit includes an experimental structure inlet total temperature probe and a comb tooth seal inlet total temperature probe.

5. The experimental structure for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 4, characterized in that: The stator casing (1), the moving blade casing (2) and the rotor (3) are all split assembly structures.

6. The experimental structure for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 4, characterized in that: The stator casing (1), the moving blade casing (2) and the rotor (3) are divided into two symmetrical parts and connected by bolts. The stator casing (1) and the moving blade casing (2) are connected by flanges and bolts.

7. The experimental structure for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 4, characterized in that: The stator casing (1), the crowned stator blades (4), and the sealing bushing (7) are all connected via a slide groove structure, and the comb tooth sealing body (8) and the annular cavity (31) are connected via a slide groove structure.

8. The experimental structure for studying the influence of the comb seal bleed air jet structure on the compressor performance according to claim 4, characterized in that: The two sides of the sealing bushing (7) are provided with a grate seal inlet static pressure detection hole and a grate seal outlet static pressure detection hole at intervals along the circumference thereof. The grate seal inlet static pressure probe and the grate seal outlet static pressure probe are installed in the grate seal inlet static pressure detection hole and the grate seal outlet static pressure detection hole respectively. The cavity inlet side of the sealing bushing (7) is also provided with a grate seal inlet total pressure detection hole and a grate seal inlet total temperature detection hole at intervals. The grate seal inlet total pressure probe and the grate seal inlet total temperature probe are correspondingly installed in the grate seal inlet total pressure probe hole and the grate seal inlet total temperature probe hole. The bottom of some of the crowned stationary blades (4) is provided with an annular pressure equalizing cavity static pressure probe hole. The annular pressure equalizing cavity static pressure probe is correspondingly installed in the annular pressure equalizing cavity static pressure probe hole. The moving blade casing (2) is provided with a moving blade front static pressure probe hole. A pressure probe is installed in the static pressure probe hole in front of the moving blade. The static pressure probe hole at the leading edge of the crowned stator blade and the static pressure probe hole at the trailing edge of the crowned stator blade are arranged on the stator casing (1). The static pressure probe at the leading edge of the crowned stator blade and the static pressure probe at the trailing edge of the crowned stator blade are installed in the static pressure probe hole at the leading edge of the crowned stator blade and the static pressure probe at the trailing edge of the crowned stator blade respectively. The moving blade casing (2) is also provided with an experimental structure inlet total pressure probe hole and an experimental structure inlet total temperature probe hole. The experimental structure inlet total pressure probe and the experimental structure inlet total temperature probe are installed in the experimental structure inlet total pressure probe hole and the experimental structure inlet total temperature probe respectively. A five-hole pneumatic probe hole and a displacement mechanism thereof are arranged on the hub flange of the outlet of the crowned stator blade. The total pressure probe at the outlet of the crowned stator blade is installed in the five-hole pneumatic probe hole for detecting the aerodynamic parameters of the outlet of the crowned stator blade.

Images