CN116399526A - Circumferential sealing effect verification device for guide vane of aero-engine - Google Patents
Circumferential sealing effect verification device for guide vane of aero-engine Download PDFInfo
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- CN116399526A CN116399526A CN202310652597.7A CN202310652597A CN116399526A CN 116399526 A CN116399526 A CN 116399526A CN 202310652597 A CN202310652597 A CN 202310652597A CN 116399526 A CN116399526 A CN 116399526A
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- 238000007789 sealing Methods 0.000 title claims abstract description 153
- 230000000694 effects Effects 0.000 title claims abstract description 37
- 238000012795 verification Methods 0.000 title abstract description 13
- 238000005192 partition Methods 0.000 claims abstract description 12
- 238000009423 ventilation Methods 0.000 claims description 34
- 238000009434 installation Methods 0.000 claims description 19
- 230000003068 static effect Effects 0.000 claims description 8
- 210000001503 joint Anatomy 0.000 claims description 4
- 238000012545 processing Methods 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 238000012360 testing method Methods 0.000 description 14
- 238000013461 design Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 4
- 230000000903 blocking effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000004576 sand Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Gasket Seals (AREA)
Abstract
The application provides a circumferential sealing effect verification device for guide blades of an aero-engine, which belongs to the technical field of sealing structures of aero-engines and specifically comprises an inner ring, an outer ring and two opposite annular plates, wherein an intermediate ring is arranged between the outer ring and the inner ring; a plurality of radially distributed partition plates are arranged between the middle ring and the inner ring, the plurality of partition plates are uniformly distributed along the circumferential direction, the middle ring and the inner ring are divided into a plurality of air outlet cavities, the middle ring, the outer ring and the annular plate enclose an air inlet cavity, an air inlet pipe communicated with the air inlet cavity is arranged on the annular plate, each air outlet cavity is communicated with an exhaust pipe, the exhaust pipes are arranged on the annular plate, and the air inlet pipes and/or the exhaust pipes are connected with flow meters; the middle ring of the air outlet cavity is detachably connected with a mounting assembly, and sealing grooves of the mounting assemblies in different air outlet cavities are different in structure and are used for mounting sealing sheets in different forms. Through the processing scheme of this application, improve the verification efficiency of seal structure.
Description
Technical Field
The application relates to the field of aeroengine sealing structures, in particular to an aeroengine guide vane circumferential sealing effect verification device.
Background
The sealing technology is an important component of the research and development work of the high-performance aeroengine, and the advanced sealing technology is a key technology for meeting the targets of the fuel consumption rate, the thrust weight ratio, the pollutant emission, the durability and the life cycle cost of the engine. By reducing the amount of leakage of the air flow inside the engine, the performance and efficiency of the engine can be greatly improved. The sealing structural design of the engine guide vane is generally inherited to the existing design, or is structurally improved on the existing design, and after improvement, a test platform directly used for verifying the sealing effect is lacking, so that leakage conditions need to be indirectly analyzed on a large-scale test piece through a flow test. Such a verification method requires that the sealing structure is mounted on the test piece, and the mounting process and the starting process are complicated and have high cost. And only one structure can be verified at a time, so that the verification efficiency is low.
Disclosure of Invention
In view of this, this application provides an aeroengine guide vane circumference sealing effect verifying attachment, has solved the problem among the prior art, improves the verification efficiency of sealing structure.
The application provides a device for verifying circumferential sealing effect of guide vane of aeroengine adopts following technical scheme:
the device comprises an inner ring, an outer ring and two opposite annular plates, wherein inner rings of the two annular plates are in sealing connection through the inner ring, the outer ring is detachably fixed on outer rings of the two annular plates, an intermediate ring is arranged between the outer ring and the inner ring, and two end faces of the intermediate ring are respectively in sealing connection with the two annular plates;
a plurality of radially distributed partition plates are arranged between the middle ring and the inner ring, the plurality of partition plates are uniformly distributed along the circumferential direction, the space between the middle ring and the inner ring is divided into a plurality of independent air outlet cavities by the plurality of partition plates, the middle ring, the outer ring and the annular plate enclose an air inlet cavity, an air inlet pipe communicated with the air inlet cavity is arranged on the annular plate, each air outlet cavity is communicated with an exhaust pipe, the exhaust pipes are arranged on the annular plate, and a flowmeter is connected on the air inlet pipe and/or the exhaust pipe;
every detachably is connected with the installation component on the intermediate ring that the chamber of giving vent to anger corresponds, be equipped with the groove of sealing on the installation component, the groove of sealing intercommunication advances the chamber with give vent to anger the chamber, the groove of sealing is used for installing the piece of sealing, different the groove structure of sealing of installation component in the chamber of giving vent to anger is different for install the piece of sealing of different forms.
Optionally, an annular boss is arranged on one side of the middle ring, which is opposite to the inner ring, the boss and the annular plate are arranged at intervals, a plurality of strip-shaped ventilation grooves which are uniformly distributed along the circumferential direction and are arranged at intervals are formed in the boss, the ventilation grooves are positioned on the boss corresponding to the air outlet cavity, the ventilation grooves penetrate through the boss and the middle ring along the radial direction of the middle ring, the length direction of the ventilation grooves is parallel to the axial direction of the middle ring, and each ventilation groove is internally provided with a mounting assembly;
the installation component is equipped with the seal half groove including two blocks of sealing of symmetry on two the side that the block is relative is sealed, two after the block butt joint is sealed, two the seal half groove is constituteed and is formed the seal groove, the seal groove is used for assembling the piece of sealing, the block of sealing be close to the side of outer loop and be close to on the side of inner loop be equipped with the ventilation slit of seal groove intercommunication, the block of sealing demountable installation is on the boss.
Optionally, the sealing block comprises a connecting plate and a plugging part arranged in the ventilation groove, wherein the connecting plate is connected with one end of the plugging part, and the connecting plate is fixed on the boss through a bolt.
Optionally, the installation component still includes the sealing washer, the sealing washer snare is established two behind the butt joint of sealing piece two the periphery of shutoff portion, the sealing washer is used for sealing the clearance between shutoff portion and the ventilation groove.
Optionally, the shutoff portion is equipped with two sand grip of parallel on the lateral wall towards the ventilation groove inner wall, the sand grip distributes on the lateral wall of shutoff portion along the circumference direction of ventilation groove, the sealing washer is installed between two sand grip.
Optionally, the partition plate is provided with 4, and each air outlet cavity is provided with 6 ventilation grooves.
Optionally, static pressure measuring points are arranged on the air inlet cavity and each air outlet cavity.
In summary, the present application includes the following beneficial technical effects:
this application divide into a plurality of air-out chambers with a device, through opening the outer loop, can install different installation component and sealing piece on the air-out chamber, install the sealing structure of different forms on different air-out chambers, advance air from the air inlet chamber, compare the air current velocity or the atmospheric pressure of different air-out chambers to the advantage of the sealing effect of the sealing structure of different forms that can be quick is arrived. The sealing effect of some form of sealing structure can also be evaluated by comparing the airflow rate or air pressure parameters of the air inlet cavity and the single air outlet cavity.
The utility model discloses a can mould according to current sealing module and process the different installation component that forms to different sealing structures, verify the sealing effect of different sealing structural style fast, quantitatively show the influence of factors such as sealing groove form, sealing piece material, offset, thickness to the sealing effect for support turbine blade's sealing structural improvement design.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic outline structure diagram of a circumferential sealing effect verification device of a guide vane of an aeroengine;
FIG. 2 is a schematic diagram of the overall structure of a circumferential sealing effect verification device for a guide vane of an aeroengine;
FIG. 3 is a schematic view of the mounting assembly and seal of the present application mounted on an intermediate ring;
FIG. 4 is a schematic view of the overall structure of the mounting assembly of the present application;
fig. 5 is a schematic structural view of the seal half groove of the present application.
Reference numerals illustrate: 1. an inner ring; 2. an outer ring; 3. an annular plate; 4. an intermediate ring; 41. a boss; 42. a vent groove; 5. a partition plate; 6. an air inlet cavity; 61. an air inlet pipe; 7. an air outlet cavity; 71. an exhaust pipe; 8. sealing blocks; 81. sealing the half groove; 82. ventilation slits; 83. a connecting plate; 84. a convex strip; 85. a blocking part; 9. and (5) static pressure measuring points.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides an aeroengine guide vane circumference sealing effect verifying device.
As shown in fig. 1 and 2, the circumferential sealing effect verification device for the guide vane of the aero-engine comprises an inner ring 1, an outer ring 2 and two opposite annular plates 3, wherein the inner rings of the two annular plates 3 are in sealing connection through the inner ring 1, the outer ring 2 is detachably fixed on the outer rings of the two annular plates 3, an intermediate ring 4 is arranged between the outer ring 2 and the inner ring 1, and two end faces of the intermediate ring 4 are respectively in sealing connection with the two annular plates 3. The contact position of the outer ring 2 and the annular plate 3 is provided with a sealing rubber ring, and the connection position of the outer ring 2 and the annular plate 3 is sealed.
A plurality of spacing plates 5 which are distributed along the radial direction are arranged between the middle ring 4 and the inner ring 1, a plurality of spacing plates 5 are uniformly distributed along the circumferential direction, a plurality of spacing plates 5 divide the space between the middle ring 4 and the inner ring 1 into a plurality of independent air outlet cavities 7, the middle ring 4, the outer ring 2 and the annular plate 3 enclose into an air inlet cavity 6, an air inlet pipe 61 communicated with the air inlet cavity 6 is arranged on the annular plate 3, an exhaust pipe 71 communicated with the corresponding air outlet cavity 7 is arranged in the area of the annular plate 3 corresponding to each air outlet cavity 7, and a flowmeter is connected on the air inlet pipe 61 and/or the exhaust pipe 71.
The middle ring 4 corresponds every detachably is connected with the installation component on the region of the chamber 7 of giving vent to anger, be equipped with the seal groove on the installation component, seal groove intercommunication air inlet chamber 6 and the chamber 7 of giving vent to anger, seal groove is used for installing the piece of sealing, different the seal groove structure of installation component in the chamber 7 of giving vent to anger is different for install the structure of sealing of different forms.
This application divide into a plurality of air-out chamber 7 with a device, through opening outer loop 2, can install different installation component and sealing piece on the air-out chamber, install the sealing structure of different forms on the different air-out chamber 7, advance air from air inlet chamber 6, compare the air current velocity or the atmospheric pressure of different air-out chamber 7 to the advantage of the sealing effect of the sealing structure of different forms that can be quick is obtained. The sealing effect of some form of sealing structure can also be evaluated by comparing the airflow rate or air pressure parameters of the air inlet chamber 6 and the individual air outlet chambers 7. The utility model discloses a can mould according to current sealing module and process the different installation component that forms to different sealing structures, verify the sealing effect of different sealing structural style fast, quantitatively show the influence of factors such as sealing groove form, sealing piece material, offset, thickness to the sealing effect for support turbine blade's sealing structural improvement design.
As shown in fig. 3, fig. 4 and fig. 5, an annular boss 41 is disposed on one side of the middle ring 4 opposite to the inner ring 1, the bosses 41 and the annular plates 3 are disposed at intervals, a plurality of elongated ventilation slots 42 which are uniformly distributed along the circumferential direction and are disposed at intervals are disposed on the bosses 41, the ventilation slots 42 are disposed on the bosses 41 corresponding to the air outlet cavities 7, the ventilation slots 42 penetrate through the bosses 41 and the middle ring 4 along the radial direction of the middle ring 4, the length direction of the ventilation slots 42 is parallel to the axial direction of the middle ring 4, and a mounting assembly is mounted in each ventilation slot 42.
The mounting assembly comprises two symmetrical sealing blocks 8, sealing half grooves 81 are formed in opposite side surfaces of the two sealing blocks 8, after the two sealing blocks 8 are in butt joint, the two sealing half grooves 81 form a sealing groove, and the sealing groove is used for assembling sealing sheets; the sealing groove and the sealing piece are matched with each other in a design structure; the side of the sealing block 8, which is close to the outer ring 2, and the side of the sealing block, which is close to the inner ring 1, are provided with ventilation slits 82 communicated with the sealing grooves, and the sealing block 8 is detachably arranged on the boss 41.
The design of boss 41 satisfies the installation of the sealing piece 8 of different structures, guarantees that all sealing pieces can not stretch into the air cavity, makes test condition unified, and boss 41 sets up with annular plate 3 interval moreover, and annular plate 3 is connected to only intermediate ring 4, and thinner intermediate ring 4 is convenient with annular plate 3 sealing connection, reduces the processing degree of difficulty.
The sealing block 8 comprises a connecting plate 83 and a blocking portion 85 arranged in the ventilation groove 42, the connecting plate 83 is connected with one end of the blocking portion 85, and the connecting plate 83 is fixed on the boss 41 through a bolt. The sealing piece 8 is a bar or forging piece of 1Cr11Ni2W2MoV, and the sealing piece is a strip of 0Cr18Ni9 or 1Cr11Ni2W2 MoV.
The mounting assembly further comprises a sealing ring sleeved on the peripheries of the two plugging portions 85 after the two plugging blocks 8 are abutted, and the sealing ring is used for sealing a gap between the plugging portions 85 and the ventilation groove 42. The sealing ring is a rubber product.
The side wall of the plugging portion 85 facing the inner wall of the ventilation groove 42 is provided with two parallel raised strips 84, the raised strips are distributed on the side wall of the plugging portion 85 along the circumferential direction of the ventilation groove 42, and the sealing ring is installed between the two raised strips 84. The two raised strips 84 limit the displacement of the sealing ring, stabilize the position of the sealing ring and stabilize the sealing effect of the sealing ring.
The relevant experimental study that this application aeroengine guide vane circumference sealing effect verifying attachment can verify has: 1) Seal groove form verification test: the influence of a straight sealing groove or a sealing groove with radian on the sealing effect is adopted; the influence on the sealing effect when certain dislocation is generated between the adjacent sealing half grooves 81; the effect of the width and depth of the sealing groove on the sealing effect. 2) And (3) verifying the section form of the sealing piece: the sealing effect of the sectional sealing piece, the arc sealing piece, the flat sealing piece and the like under different sealing groove forms; study on sealing effect of different sealing piece thicknesses under different sealing groove forms; 3) And (3) verification test of sealing sheet materials: sealing effect of the sealing piece and the flexible sealing piece made of conventional metal sheet materials in different sealing grooves and sealing piece section states; 4) And (3) a seal effect research test of the innovative seal structure.
In one embodiment, the partition plates 5 are provided with 4, and each air outlet cavity 7 is provided with 6 ventilation slots 42. In the embodiment of the present application, 4 air inlet pipes 61 uniformly distributed in the circumferential direction are provided on the annular plate 3.
And static pressure measuring points 9 are arranged on the air inlet cavity 6 and each air outlet cavity 7. The air inlet cavity 6 is provided with 8 static pressure measuring points 9, and the static pressure measuring points 9 of the air inlet cavity 6 are arranged on the outer ring 2; each air outlet cavity 7 is provided with 2 static pressure measuring points 9, and the static pressure measuring points 9 on the air outlet cavities 7 are arranged on the inner ring 1.
The embodiment of the application provides a test method, and a transformation ratio test is as follows:
test piece status: the inlet is ventilated and the outlet is vented to atmosphere. And (3) a test module: and sealing the structural module. Inlet pressure: 110kPa (kilopascal), 130kPa, 150kPa, 170kPa, 200kPa, 250kPa, 300kPa, 350kPa. The inlet flow, temperature, pressure and pressures of the inlet chamber 6 and the outlet chamber 7 under the pressure conditions are recorded.
The embodiment of the application also provides a test method, and the differential pressure test is as follows:
test piece status: the inlet is ventilated, and the outlet is connected with a regulating valve. And (3) a test module: and sealing the structural module. Pressure ratio of the gas collection chamber: average pressure of intake chamber 6/average pressure of exhaust chamber 7 = 1.03, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6. Intake chamber 6 average pressure: 200kPa (kilopascal), 250kPa, 300kPa, 350kPa. The inlet flow, temperature, pressure and pressures of the inlet chamber 6 and the outlet chamber 7 under the pressure conditions are recorded.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The device is characterized by comprising an inner ring, an outer ring and two opposite annular plates, wherein the inner rings of the two annular plates are connected in a sealing way through the inner ring, the outer ring is detachably fixed on the outer rings of the two annular plates, an intermediate ring is arranged between the outer ring and the inner ring, and two end faces of the intermediate ring are respectively connected with the two annular plates in a sealing way;
a plurality of radially distributed partition plates are arranged between the middle ring and the inner ring, the plurality of partition plates are uniformly distributed along the circumferential direction, the space between the middle ring and the inner ring is divided into a plurality of independent air outlet cavities by the plurality of partition plates, the middle ring, the outer ring and the annular plate enclose an air inlet cavity, an air inlet pipe communicated with the air inlet cavity is arranged on the annular plate, each air outlet cavity is communicated with an exhaust pipe, the exhaust pipes are arranged on the annular plate, and a flowmeter is connected on the air inlet pipe and/or the exhaust pipe;
every detachably is connected with the installation component on the intermediate ring that the chamber of giving vent to anger corresponds, be equipped with the groove of sealing on the installation component, the groove of sealing intercommunication advances the chamber with give vent to anger the chamber, the groove of sealing is used for installing the piece of sealing, different the groove structure of sealing of installation component in the chamber of giving vent to anger is different for install the piece of sealing of different forms.
2. The device for verifying the circumferential sealing effect of the aeroengine guide vane according to claim 1, wherein an annular boss is arranged on one side of the middle ring, which is opposite to the inner ring, the boss and the annular plate are arranged at intervals, a plurality of strip-shaped ventilation grooves which are uniformly distributed along the circumferential direction and are arranged at intervals are formed in the boss, the ventilation grooves are positioned on the boss corresponding to the air outlet cavity, the ventilation grooves penetrate through the boss and the middle ring along the radial direction of the middle ring, the length direction of the ventilation grooves is parallel to the axial direction of the middle ring, and a mounting assembly is arranged in each ventilation groove;
the installation component is equipped with the seal half groove including two blocks of sealing of symmetry on two the side that the block is relative is sealed, two after the block butt joint is sealed, two the seal half groove is constituteed and is formed the seal groove, the seal groove is used for assembling the piece of sealing, the block of sealing be close to the side of outer loop and be close to on the side of inner loop be equipped with the ventilation slit of seal groove intercommunication, the block of sealing demountable installation is on the boss.
3. The device for verifying the circumferential sealing effect of an aeroengine guide vane according to claim 2, wherein the sealing block comprises a connecting plate and a sealing part arranged in the ventilation groove, the connecting plate is connected with one end of the sealing part, and the connecting plate is fixed on the boss through a bolt.
4. The device for verifying circumferential sealing effect of an aircraft engine guide vane according to claim 3, wherein the mounting assembly further comprises a sealing ring sleeved on the outer circumferences of the two plugging portions after the two plugging pieces are butted, and the sealing ring is used for sealing a gap between the plugging portions and the ventilation groove.
5. The device for verifying the circumferential sealing effect of an aircraft engine guide vane according to claim 4, wherein two parallel raised strips are arranged on the side wall of the plugging part facing the inner wall of the ventilation groove, the raised strips are distributed on the side wall of the plugging part along the circumferential direction of the ventilation groove, and the sealing ring is arranged between the two raised strips.
6. The device for verifying the circumferential sealing effect of a guide vane of an aeroengine according to claim 2, wherein 4 partition plates are provided, and 6 ventilation grooves are provided in each air outlet cavity.
7. The device for verifying the circumferential sealing effect of the guide vane of the aeroengine according to claim 1, wherein the air inlet cavity and each air outlet cavity are provided with static pressure measuring points.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310652597.7A CN116399526B (en) | 2023-06-05 | 2023-06-05 | Circumferential sealing effect verification device for guide vane of aero-engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310652597.7A CN116399526B (en) | 2023-06-05 | 2023-06-05 | Circumferential sealing effect verification device for guide vane of aero-engine |
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| CN116399526A true CN116399526A (en) | 2023-07-07 |
| CN116399526B CN116399526B (en) | 2023-09-01 |
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