CN112594014B - A air feeder that seals for transonic turbine plane cascade experiment - Google Patents
A air feeder that seals for transonic turbine plane cascade experiment Download PDFInfo
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- CN112594014B CN112594014B CN202011479189.9A CN202011479189A CN112594014B CN 112594014 B CN112594014 B CN 112594014B CN 202011479189 A CN202011479189 A CN 202011479189A CN 112594014 B CN112594014 B CN 112594014B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
The invention discloses a sealed air supply device for transonic turbine plane cascade experiments, wherein transonic turbine blade cascades are arranged on a wind tunnel end wall, a sealed air supply cavity is arranged on the outer side of the wind tunnel end wall, a sealed air outlet which extends along a direction vertical to a main flow and is positioned at the upstream position of a front edge of the transonic turbine blade cascade is arranged at the top of the sealed air supply cavity, and sealed cold air flowing out of the sealed air outlet has a component velocity vertical to the main flow direction, is introduced into a main flow channel of the wind tunnel and interacts with main flow gas in the wind tunnel. The characteristic that the speed direction of cold air in the sealed air supply cavity is tangent to the circumferential direction of the transonic turbine blade grid is utilized, the circumferential speed of sealed flow can be reproduced without rotating parts, the effects of independently changing the flow rate of the sealed flow and the circumferential speed of the sealed flow are achieved, sealed jet flow conditions required by a transonic turbine plane blade grid experiment can be fully simulated, the characteristics of the sealed flow inside a real turbine are reproduced, and a more accurate three-dimensional flow field structure is easily obtained.
Description
Technical Field
The invention belongs to the field of transonic turbine plane cascade experiments of aero-engines/gas turbines, and relates to a sealed gas supply device for transonic turbine plane cascade experiments. According to the invention, by utilizing the characteristic that the speed direction of cold air in the sealed air supply cavity is tangential to the circumferential direction of the transonic turbine blade cascade, the circumferential speed of a sealed flow can be reproduced without rotating parts, and meanwhile, the effects of independently changing the flow rate and the circumferential speed of the sealed flow are realized, the sealed jet flow conditions required by a transonic turbine plane blade cascade experiment are fully simulated, and the turbine sealing experiment cost can be greatly reduced.
Background
In modern advanced aircraft engines, a large amount of cooling gas and containment gas is required to ensure safe operation of the high pressure turbine. However, the sealing flow can generate complex interaction with the main flow in the turbine channel while ensuring the normal operation of the engine, and further has great influence on the performance of the turbine. The influence of the turbine rim seal flow on the mainstream flow characteristics and the turbine performance becomes an important issue which must be considered in the turbine refinement design. Most of the existing turbine sealing experiments are performed on a turbine-grade component experiment table or a low-speed large-size rotating experiment table, although the influence characteristics of real sealing flow on mainstream can be obtained by performing the whole-grade experiment on the turbine, the whole-grade experiment has high requirements on laboratory equipment and instruments, the experiment cost is high, and the realization of the fine measurement difficulty of the internal flow field of the turbine-grade channel is high. In comparison, the plane blade cascade can conveniently, quickly and economically research some basic flow phenomena in the turbine, has the characteristics of low cost, easiness in measurement, convenience and controllability and the like, is always an important means for researching the flow in the impeller machine, but the sealing flow in the real engine is complex rotary flow and has larger axial, radial and circumferential speeds, but the sealing flow is limited by the fact that the plane blade cascade does not have a rotating part, the jet flow conditions of the sealing flow of the turbine of the real engine are difficult to reproduce in the plane blade cascade experiment, particularly the circumferential speed of the sealing flow is difficult to simulate, and the understanding of the interaction mechanism of the sealing flow and the main flow of the real turbine is severely limited. Therefore, it is very necessary to design a sealing air supply device capable of being applied to a transonic turbine plane cascade experiment table, so that the sealing air supply device can reproduce the sealing flow characteristics in a real turbine, a more accurate three-dimensional flow field structure is easy to obtain, the experiment cost can be saved, and the measurement difficulty can be reduced.
Disclosure of Invention
Aiming at the technical problems in the prior art, the invention aims to provide a sealing air supply device applied to a transonic turbine plane blade cascade experiment, by utilizing the characteristic that the speed direction of cold air in a sealing air supply cavity is tangential to the circumferential direction of a transonic turbine blade cascade, the circumferential speed of sealing flow can be reproduced without rotating parts, the effects of independently changing the flow rate and the circumferential speed of the sealing flow are realized, the sealing jet flow conditions required by the transonic turbine plane blade cascade experiment can be fully simulated, the sealing flow characteristics in a real turbine are reproduced, a more accurate three-dimensional flow field structure is easily obtained, the experiment cost can be saved, and the measurement difficulty is reduced.
The technical scheme adopted by the invention for realizing the technical purpose is as follows:
a sealed air supply device applied to transonic turbine plane cascade experiments comprises transonic turbine cascade blades which are positioned in a main flow channel of a wind tunnel and vertically arranged on an end wall of the wind tunnel, and is characterized in that,
the sealing air supply cavity is arranged on the outer side of the end wall of the wind tunnel and extends perpendicular to the main flow direction, an air inlet pipeline communicated with a sealing air source is arranged at one end of the sealing air supply cavity, an air outlet pipeline communicated with the external environment is arranged at the other end of the sealing air supply cavity, the flow direction of sealing air in the sealing air supply cavity is perpendicular to the main flow direction, a slit extending in the direction perpendicular to the main flow direction and located at the upstream position of the front edge of the transonic turbine blade grid is arranged on a top cover plate of the sealing air supply cavity, a sealing structure is arranged at the slit, the slit forms a sealing air outlet, and sealing air flowing out of the sealing air outlet has the component velocity perpendicular to the main flow direction, is introduced into the main flow channel of the wind tunnel and interacts with main flow gas in the main flow channel.
Preferably, an inlet end of the main flow channel of the wind tunnel is communicated with a main flow air source, and the main flow air source is a high-pressure high-speed air source generated by a centrifugal air compressor.
Preferably, the main flow channel of the wind tunnel is provided with a contraction section for flow acceleration of the main flow gas.
Furthermore, the wind tunnel main flow channel is at least provided with a first-stage contraction section and a second-stage contraction section which are arranged along the flow direction, and the air flow passes through the first-stage contraction section and the second-stage contraction section to realize two-time flow acceleration.
Preferably, a plurality of rows of wall surface air extraction holes which are positioned at the upstream of the transonic turbine blade cascade and are communicated with the external environment are formed in the end wall of the wind tunnel, and low-energy fluid in the boundary layer of the inflow end region is discharged from the wall surface air extraction holes under the action of pressure difference between main flow and the external atmosphere so as to reduce the thickness of the boundary layer of the inflow end region.
Preferably, a preferably adjustable-angle tail plate is arranged at a position downstream of the transonic turbine blade row, and the exhaust gas from the transonic turbine blade row is discharged to the atmosphere through the tail plate.
Preferably, the sealing and sealing structure comprises a left sealing plate and a right sealing plate which are positioned on two sides of the slit, the left sealing plate and the right sealing plate are detachably and fixedly arranged on the top cover plate of the sealing air supply cavity, and the top cover plate of the sealing air supply cavity and the inner side surface of the wind tunnel end wall are smooth and excessively flat. The influence rule of different sealing structures on the pneumatic performance of the turbine can be researched by replacing different sealing plates.
Furthermore, the sealing structure is a fish mouth type sealing structure.
Preferably, a honeycomb section for breaking airflow vortexes is arranged on the air inlet pipeline of the sealed air supply cavity, so that the inflow quality of sealed cold air is improved.
Preferably, a control valve is arranged on the air inlet pipeline and/or the exhaust pipeline of the sealed air supply cavity, and the sealed cold air flow of the sealed air outlet is changed by adjusting the opening degree of the control valve.
Preferably, a speed adjusting plate is arranged on the inner wall of the bottom plate of the sealed air supply cavity, one end of the speed adjusting plate is fixed, the height of the other end of the speed adjusting plate is adjustable, the flow area of the sealed air supply cavity is adjusted by changing the inclination of the speed adjusting plate, and then the partial speed of the sealed cold air at the sealed air outlet, which is perpendicular to the main flow direction, is adjusted.
Furthermore, a height adjusting mechanism is arranged outside the bottom plate of the sealed air supply cavity and used for adjusting the height of the other end of the speed adjusting plate, a sliding seat is arranged at the height of the other end of the speed adjusting plate, a sliding rail is arranged on the sliding seat, the height adjusting mechanism comprises an adjusting support fixedly arranged outside the bottom plate of the sealed air supply cavity, an adjusting rod is arranged in the adjusting support, the tail end of the adjusting rod is formed into a sliding block, the sliding block is arranged in the sliding rail on the sliding seat in a sliding mode, a rotating handle is arranged at the head of the adjusting rod, and the rotating handle is rotated to enable the adjusting rod to move up and down in the adjusting support so as to adjust the height of the other end of the speed adjusting plate.
Furthermore, be equipped with one in the regulation support and close on the direction through-hole that the bottom plate of obturating air feed chamber was arranged and one keep away from the screw hole that the bottom plate of obturating air feed chamber was arranged, adjust the pole pass the direction through-hole with the seat transmission that slides on the velocity modulation board is connected, be equipped with on the twist grip with the external screw thread section that the screw hole was mutually supported, it sets up to adjust the pole in the external screw thread section of twist grip, through rotating the twist grip makes the external screw thread section follow the screw hole reciprocates, then drives adjust the pole and reciprocate.
Furthermore, a sealing structure is arranged at the guide through hole of the adjusting bracket.
The invention relates to a sealed air supply device applied to a transonic turbine plane cascade experiment, which has the working principle that: in order to simulate the interaction characteristics of the sealing flow and the main flow of the transonic turbine, a sealing air supply cavity extending perpendicular to the main flow direction is arranged on the outer side of the wind tunnel end wall, sealing air cooling in the flow direction perpendicular to the main flow direction is introduced into the sealing air supply cavity, a slit extending perpendicular to the main flow direction and located at the upstream position of the front edge of the transonic turbine blade cascade is arranged at the top of the sealing air supply cavity to form a sealing air outlet, and the sealing air cooling flowing out of the sealing air outlet has a component velocity perpendicular to the main flow direction and is used for simulating the interaction characteristics of the circumferential sealing flow and the main flow of the transonic turbine.
Compared with the prior art, the sealed air supply device applied to the transonic turbine plane cascade experiment has the beneficial technical effects that: (1) simple structure, processing convenience, easily realization utilize the tangent characteristics of air conditioning speed direction and transonic speed turbine cascade circumferential direction in the air feed chamber that seals, need not the rotation and can reappear the circumferential speed of the stream that seals, can reduce turbine experiment cost that seals by a wide margin. (2) The opening degree of the speed adjusting plate can be controlled by adjusting the rotating handle, so that the circumferential speed of the sealing flow can be flexibly controlled; the flow of the sealing flow can be controlled by adjusting the opening degree of the inlet and outlet valves of the sealing air supply cavity, the effects of independently changing the flow of the sealing flow and the circumferential speed of the sealing flow are realized, and the sealing jet flow conditions required by the transonic turbine plane cascade experiment are fully simulated.
Drawings
FIG. 1 is a schematic view of a sealed gas supply device applied to a transonic turbine plane cascade experiment.
Fig. 2 is a top view and a partial enlarged view of fig. 1.
FIG. 3 is a schematic three-dimensional structure diagram of a turbine sealed air supply cavity.
FIG. 4 is a schematic cross-sectional view and a partial enlarged view of a turbine sealed air supply cavity.
Fig. 5 is a schematic view of the structure of the adjusting lever.
Fig. 6 is a schematic view of an adjusting bracket structure.
Fig. 7 is a schematic structural view of the rotary handle, wherein (a) is a schematic three-dimensional structure and (B) is a schematic cross-sectional structure.
Fig. 8 is a schematic structural view of the sliding seat, wherein (a) is a schematic three-dimensional structural view, and (B) is a schematic cross-sectional structural view.
Fig. 9 is a schematic view of an assembly structure, in which (a) is a schematic view of a three-dimensional structure and (B) is a schematic view of a cross-sectional structure.
The main reference symbols in the drawings are as follows:
the main air source 1, the first-stage contraction section 2, the second-stage contraction section 3, the wind tunnel end wall 4, a wall surface suction hole 5, a transonic turbine blade cascade 6, a sealing air supply cavity 7, an air inlet pipeline 8, an exhaust pipeline 9, a sealing air outlet 10, a tail plate 11, a sealing structure 12, a left sealing plate 13, a right sealing plate 14, a top cover plate 15, a honeycomb section 16, a rotating handle 17, a speed adjusting plate 18, a control valve 19, a control valve 20, an adjusting rod 21, an adjusting support 22, a sliding seat 23, a bottom plate 24, a circular boss 25, a spherical bulge 26, a cylindrical rod 27, a threaded hole 28, a through hole 29, a groove 30, a cover plate 31, an external thread 32, a cylindrical hole 33, a circular blocking cover 34, a circular cavity 35 and a circular groove 36.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The structure and technical scheme of the present invention are further described in detail with reference to the accompanying drawings, and an embodiment of the present invention is provided.
In order to simulate the interaction characteristics of transonic turbine seal flow and main flow, the invention provides a seal air supply device for transonic plane cascade experiments, which is shown in figures 1-4. The invention discloses a sealed air supply device for transonic speed plane blade grid experiments, which comprises transonic speed turbine blade grids 6 which are positioned in a wind tunnel main flow channel and vertically arranged on a wind tunnel end wall 4, wherein the inlet end of the wind tunnel main flow channel is communicated with a main air source 1, and the main air source 1 is a high-pressure high-speed air source generated by a centrifugal air compressor. The wind tunnel main flow channel is provided with a contraction section, the wind tunnel main flow channel is preferably at least provided with a first-stage contraction section 2 and a second-stage contraction section 3 which are arranged along the flow direction, and the air flow is accelerated twice through the first-stage contraction section 2 and the second-stage contraction section 3. The wind tunnel end wall 4 is provided with a plurality of rows of wall surface air extraction holes 5 which are positioned at the upstream of the transonic turbine blade cascade 6 and communicated with the external environment, and low-energy fluid in the boundary layer of the inflow end region is discharged from the wall surface air extraction holes 5 under the action of pressure difference between main flow and external atmosphere so as to reduce the thickness of the boundary layer of the inflow end region. The outer side of the wind tunnel end wall 4 is provided with a sealed air supply cavity 7 extending perpendicular to the main flow direction, one end of the sealed air supply cavity 7 is provided with an air inlet pipeline 8 communicated with a sealed air source, the other end of the sealed air supply cavity is provided with an exhaust pipeline 9 communicated with the external environment, the flow direction of sealed air in the sealed air supply cavity 7 is perpendicular to the main flow direction, a slit extending perpendicular to the main flow direction and located at the upstream position of the front edge of the transonic turbine blade grid 6 is arranged on a top cover plate 15 of the sealed air supply cavity 7, a sealed sealing structure 12 is arranged at the slit, so that the slit is formed into a sealed air outlet 10, and sealed air flowing out of the sealed air outlet 10 has a component velocity perpendicular to the main flow direction, is introduced into the main flow channel of the wind tunnel and interacts with main flow gas in the wind tunnel. A preferably angularly adjustable tail plate 11 is provided downstream of the transonic turbine blade row 6, and the exhaust gas from the transonic turbine blade row 6 is discharged through the tail plate 11 to the atmosphere.
More specifically, as shown in fig. 1 to 4, the device mainly generates a high-pressure high-speed main flow air source 1 by a centrifugal air compressor, airflow passes through a first-stage contraction section 2 and a second-stage contraction section 3 to realize two-time flow acceleration, in the process, in order to reduce the thickness of a boundary layer of an incoming flow end region, a plurality of rows of wall surface air extraction holes 5 are further arranged on end walls 4 on two sides of the wind tunnel, and low-energy fluid in the end region is discharged by utilizing the pressure difference between main flow and outside atmosphere, so that a main flow environment with better flow field quality is provided for a transonic turbine blade grid 6. The generation of the sealing flow is mainly provided by a sealing air supply cavity 7, cold air flows in from an air inlet pipeline 8, one part of cold air is discharged from an exhaust pipeline 9, the other part of cold air flows in from a sealing air outlet 10 into a transonic turbine blade cascade 6 channel, and the complex interaction is generated with the main flow, and finally the cold air is discharged into the atmospheric environment through a tail plate 11. In addition, different sealing and sealing structures 12 can have an important influence on the flow of the turbine end area, the sealing and sealing structures 12 are mainly formed by a left sealing plate 13 and a right sealing plate 14 in a surrounding mode, and the influence rule of the different sealing and sealing structures 12 on the aerodynamic performance of the turbine can be researched by replacing the different sealing plates. The left sealing plate 13 and the right sealing plate 14 are fixed on the sealing air supply cavity top cover plate 15, the sealing air supply cavity top cover plate 15 is fixed on the side end wall 4, and the sealing air supply cavity top cover plate 15 and the air hole side end wall 4 are guaranteed to be smooth and excessive.
The three-dimensional structure schematic diagram and the two-dimensional section diagram of the sealed air supply cavity 7 are respectively shown in fig. 3 and fig. 4, when cold air flows in from the air inlet pipeline 8 of the sealed air supply cavity 7, a larger vortex structure is formed, and therefore a honeycomb section 16 is arranged in the inlet pipeline 8 of the sealed air supply cavity 7 to enable the cold air to be broken in vortex, and the quality of the incoming flow of the cold air is improved. In order to reproduce the interaction environment of the sealing flow and the main flow in the real engine, two important parameters of the circumferential speed and the inlet flow of the sealing flow must be controlled, because the airflow direction in the sealing air supply cavity 7 is the same as the circumferential direction of the transonic turbine blade cascade 6, the cold air has larger circumferential speed after flowing out from the sealing air outlet 10, in addition, a speed adjusting plate 18 is arranged on the inner wall of a bottom plate 24 of the sealing air supply cavity 7, one end of the speed adjusting plate 18 is fixed, the height of the other end of the speed adjusting plate 18 can be adjusted, the inclination of the speed adjusting plate 18 can be changed by rotating a handle 17, the flow area of the sealing air supply cavity 7 is further adjusted, and therefore the circumferential speed Vt of the sealing flow can be changed. And the opening degree of a control valve 19 on the air inlet pipeline 8 and a control valve 20 on the exhaust pipeline 9 for sealing the air supply cavity can be adjusted to change the sealing air flow of the sealing air outlet 10. The rotating handle 17 and the speed adjusting plate 18 are driven by an adjusting rod 21, an adjusting bracket 22 and a sliding seat 23, wherein the adjusting bracket 22 is fixedly connected with a bottom plate 24 for sealing the air supply cavity 7.
A circular boss 25 is arranged above the adjusting rod 21, a spherical bulge 26 is arranged below the adjusting rod, and the circular boss 25 is connected with the spherical bulge 26 through a cylindrical rod 27 as shown in figure 5.
The structure of the adjusting bracket 22 is as shown in fig. 6, a threaded hole 28 is formed above the adjusting bracket 22, a through hole 29 is formed below the adjusting bracket 22, and in order to ensure that the adjusting rod 21 can move smoothly after being inserted into the through hole 29, the diameter of the through hole 29 is slightly larger than the outer diameter of the cylindrical rod 27; in order to ensure that the high-pressure cold air in the sealed air supply cavity 7 does not leak from the hole, a groove 30 is designed above the through hole for placing a sealing gasket, and a cover plate 31 is arranged above the groove for extruding the sealing gasket to realize the sealing purpose.
The structure of the rotating handle 17 is schematically shown in fig. 7, the outer side of the rotating handle 17 is designed with an external thread 32, the size of the external thread is tightly matched with that of the threaded hole 28, the inner part of the rotating handle is designed with a cylindrical hole 33, and in order to ensure that the adjusting rod 21 can freely rotate in the rotating handle 17, the inner diameter of the cylindrical hole 33 is slightly larger than the outer diameter of the cylindrical rod 27; in addition, the upper portion of the rotating handle 17 is further provided with a circular blocking cover 34, so that a circular cavity 35 is formed, and the circular boss 25 and the circular cavity 35 are in large clearance fit.
The structural schematic diagram of the sliding seat 23 is shown in fig. 8, a circular groove 36 is designed inside the sliding seat 23, the circular groove 36 and the spherical protrusion 26 form a clearance fit, so that it is ensured that the adjusting rod 21 and the sliding seat 23 can rotate relatively and slide relatively, and the sliding seat 23 is fixedly connected with the speed adjusting plate 18.
The assembly schematic diagram among the rotating handle 17, the adjusting rod 21, the sliding seat 23 and the speed adjusting plate 18 is shown in fig. 9, the upper and lower opening degrees of the speed adjusting plate 18 can be driven by rotating the rotating handle 17, so that the flow area of the sealing air supply cavity 7 is changed, and the purpose of adjusting the circumferential speed of the sealing flow is achieved. The invention can realize that the sealing flow and the circumferential speed flowing into the transonic turbine blade cascade are independently changed so as to simulate the sealing jet flow conditions required by the transonic turbine plane blade cascade experiment, and has the advantages of convenient operation and low cost.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (9)
1. A sealed air supply device for transonic turbine plane blade cascade experiments comprises transonic turbine blade cascades which are positioned in a main flow channel of a wind tunnel and vertically arranged on end walls of the wind tunnel, and is characterized in that,
a sealed air supply cavity extending perpendicular to the main flow direction is arranged on the outer side of the end wall of the wind tunnel, an air inlet pipeline communicated with a sealed air source is arranged at one end of the sealed air supply cavity, an air outlet pipeline communicated with the external environment is arranged at the other end of the sealed air supply cavity, the flow direction of sealed cold air in the sealed air supply cavity is perpendicular to the main flow direction, a slit extending perpendicular to the main flow direction and located at the upstream position of the front edge of the transonic turbine blade grid is arranged on a top cover plate of the sealed air supply cavity, a sealed sealing structure is arranged at the slit, the slit is formed into a sealed air outlet, and the sealed cold air flowing out of the sealed air outlet has a component velocity perpendicular to the main flow direction, is introduced into the main flow channel of the wind tunnel and interacts with main flow gas in the wind tunnel;
the air inlet pipeline and/or the air outlet pipeline of the sealed air supply cavity are/is provided with a control valve, and the sealed cold air flow of the sealed air outlet is changed by adjusting the opening of the control valve;
the inner wall of the bottom plate of the sealing air supply cavity is provided with a speed adjusting plate, one end of the speed adjusting plate is fixed, the height of the other end of the speed adjusting plate is adjustable, the flow area of the sealing air supply cavity is adjusted by changing the inclination of the speed adjusting plate, and then the sub-speed of the sealing air outlet of the sealing air conditioner perpendicular to the main flow direction is adjusted.
2. The sealing air supply device for the transonic turbine plane cascade experiment as claimed in claim 1, wherein an inlet end of the main flow channel of the wind tunnel is communicated with a main flow air source, and the main flow air source is a high-pressure high-speed air source generated by a centrifugal air compressor.
3. The sealing air supply device for the transonic turbine plane cascade experiment as claimed in claim 1, wherein the wind tunnel main flow channel is provided with a contraction section, and the contraction section comprises a first stage contraction section and a second stage contraction section which are arranged along the flow direction and used for accelerating the flow of main flow gas.
4. The sealing air supply device for the transonic turbine plane cascade experiment as claimed in claim 1, wherein a plurality of rows of wall surface air extraction holes which are located at the upstream of the transonic turbine blade cascade and are communicated with the external environment are arranged on the end wall of the wind tunnel, and low-energy fluid in the boundary layer of the inflow end region is discharged from the wall surface air extraction holes under the action of pressure difference between main flow and external atmosphere so as to reduce the thickness of the boundary layer of the inflow end region.
5. The seal air supply device for the transonic turbine blade cascade test according to claim 1, wherein an angle-adjustable tail plate is arranged at a downstream position of the transonic turbine blade cascade, and the exhaust gas from the transonic turbine blade cascade flows through the tail plate and is exhausted to the atmosphere.
6. The sealing air supply device for the transonic turbine plane cascade experiment of claim 1, wherein the sealing structure comprises a left sealing plate and a right sealing plate which are positioned on two sides of the slit, the left sealing plate and the right sealing plate are fixedly arranged on a top cover plate of the sealing air supply cavity in a detachable mode, the top cover plate of the sealing air supply cavity and the inner side surface of the wind tunnel end wall are in smooth and smooth transition, and the influence rule of different sealing structures on the turbine aerodynamic performance can be researched by replacing different sealing plates.
7. The sealed air supply device for the transonic turbine plane cascade experiment as claimed in claim 1, wherein a honeycomb section for breaking airflow vortexes is arranged on an air inlet pipeline of the sealed air supply cavity, so that inflow quality of sealed cold air is improved.
8. The seal gas supply device for the transonic turbine plane cascade experiment according to claim 1, it is characterized in that a height adjusting mechanism is arranged outside the bottom plate of the sealing air supply cavity and used for adjusting the height of the other end of the speed adjusting plate, a sliding seat is arranged at the other end of the speed adjusting plate in height, a sliding rail is arranged on the sliding seat, the height adjusting mechanism comprises an adjusting bracket fixedly arranged outside the bottom plate of the sealed air supply cavity, an adjusting rod is arranged in the adjusting bracket, the tail end of the adjusting rod is formed into a sliding block, the sliding block is arranged in a sliding rail on the sliding seat in a sliding way, the head part of the adjusting rod is provided with a rotating handle, the adjusting rod moves up and down in the adjusting bracket by rotating the rotating handle so as to adjust the height of the other end of the speed adjusting plate.
9. The sealing air supply device for the transonic turbine plane cascade experiment as claimed in claim 8, wherein a guiding through hole arranged close to the bottom plate of the sealing air supply chamber and a threaded hole arranged far away from the bottom plate of the sealing air supply chamber are arranged in the adjusting bracket, the adjusting rod penetrates through the guiding through hole to be in transmission connection with the sliding seat on the speed adjusting plate, an external threaded section matched with the threaded hole is arranged on the rotating handle, the adjusting rod is arranged in the external threaded section of the rotating handle, and the external threaded section moves up and down along the threaded hole by rotating the rotating handle, so as to drive the adjusting rod to move up and down.
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| CN114034460B (en) * | 2021-11-10 | 2023-08-22 | 中国人民解放军空军工程大学 | Secondary flow generating device |
| CN114856719A (en) * | 2022-04-18 | 2022-08-05 | 中国航发沈阳发动机研究所 | Universal air system, structure and control method for turbine rotor test |
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| JP5818717B2 (en) * | 2012-02-27 | 2015-11-18 | 三菱日立パワーシステムズ株式会社 | gas turbine |
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