CN112179671A - Low-pressure turbine annular cascade test bed with unsteady wake simulation function - Google Patents
Low-pressure turbine annular cascade test bed with unsteady wake simulation function Download PDFInfo
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- CN112179671A CN112179671A CN202011059554.0A CN202011059554A CN112179671A CN 112179671 A CN112179671 A CN 112179671A CN 202011059554 A CN202011059554 A CN 202011059554A CN 112179671 A CN112179671 A CN 112179671A
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- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a low-pressure turbine annular cascade test bed with unsteady wake simulation function, which at least comprises a low-pressure turbine annular cascade, a turbine guide vane ring coaxially arranged at the upstream of the low-pressure turbine annular cascade, a cylindrical rod turntable axially arranged between the low-pressure turbine annular cascade and the turbine guide vane ring, and a plurality of cylindrical rods uniformly arranged on the edge of the cylindrical rod turntable along the circumferential direction, wherein the sizes of the wire diameters of turbulent flow grids are adjusted by respectively utilizing the rotation of the cylindrical rods and the annular cascade, changing the rotating speed of a motor and the distance between spokes, the distance and the installation position are adjusted, the frequency of a frequency converter of the centrifugal fan is adjusted to fully reproduce complex working environments such as upstream wake sweep, radial pressure gradient, wake sweep frequency, turbulence intensity, turbulence scale, incoming flow Reynolds number and the like in the low-pressure turbine, flow field parameters are convenient and controllable, and refined flow field measurement in the low-pressure turbine is easy to realize.
Description
Technical Field
The invention belongs to the field of unsteady tests of aero-engines/gas turbines, relates to a low-pressure turbine annular blade grid test bed, and particularly relates to a low-pressure turbine annular blade grid test bed with an unsteady wake simulation function. Because the cylindrical rod is similar in structure to the wake downstream of the blade, it is widely adopted to simulate the wake of the blade by using the cylindrical rod. The invention fully reproduces complex working environments such as upstream wake sweep, radial pressure gradient, wake sweep frequency, turbulence intensity and turbulence scale, incoming flow Reynolds number and the like in the real low-pressure turbine by respectively rotating the cylindrical rod and the annular cascade, changing the rotating speed of the motor and the distance between spokes, adjusting the wire diameter size, the distance and the mounting position of the turbulence grid and adjusting the frequency of the frequency converter of the centrifugal fan, and the flow field parameters are convenient and controllable, so that the internal refined flow field measurement of the low-pressure turbine is easy to realize.
Background
For a long time, a great deal of research work is carried out on the complex flow characteristics and loss mechanisms at the end area of the low-pressure turbine in a steady environment, but the unsteady flow effect inherent in the low-pressure turbine is ignored. The aerodynamic thermodynamic characteristics of the multistage low-pressure turbine of the civil large bypass ratio turbofan engine determine that the main unsteady flow phenomenon and the effect thereof in the turbine must be considered in the aerodynamic design of the high-load low-pressure turbine. The unsteady effects of the upstream wake have been identified by many researchers as one of the most important unsteady mechanisms inside axial flow turbines, especially inside low pressure turbines. The unsteady nature of the wake sweep underlying the boundary layer development suggests that the upstream wake may influence the formation and development of the end region secondary flow by interfering with the interaction between the boundary layer and the end region secondary flow. However, it is noteworthy that: although the influence of the upstream wake on the unsteady flow at the end region of the low-pressure turbine has attracted attention in recent years, most of the experiments and calculation works are carried out on a planar cascade, the planar cascade experiment can conveniently, quickly and economically research some basic flow phenomena in the low-pressure turbine, but the planar cascade experiment is limited by two-dimensional flow, the radial pressure gradient in a low-pressure turbine blade channel of a real engine cannot be reproduced by the planar cascade experiment, and the complicated three-dimensional flow characteristic in the impeller machinery cannot be accurately obtained. In the real low-pressure turbine, due to the curvature of the annular end walls of the hub and the casing, the pressure gradient in the turbine is not only the transverse pressure difference from the pressure surface to the suction surface, but also the radial pressure gradient from the casing to the hub, so that the pressure gradient in the blade channel is asymmetrically distributed along the middle section, and the radial pressure gradient can directly influence the development of the vortex system structures such as horseshoe vortex, channel vortex, trailing edge shedding vortex and the like in the end region, which is the main reason for causing the secondary flow in the planar blade grid end region to be different from that of the real low-pressure turbine.
Although the actual aerodynamic characteristics of the impeller machinery can be obtained by carrying out the whole-stage experiment on the low-pressure turbine, the whole-stage experiment has high requirements on laboratory equipment and instruments, the experiment cost is high, and the difficulty in realizing the fine measurement of the flow field in the turbine stage channel is high. Compared with the prior art, the annular blade cascade experiment can simulate the radial pressure gradient and radial secondary flow in the impeller machinery more truly, and can also consider the distortion, rotation and the like of the boundary layer at the inlet end area of the actual blade cascade.
Disclosure of Invention
Aiming at the defects and shortcomings in the prior art, the invention aims to provide a low-pressure turbine annular blade grid test bed with an unsteady wake simulation function, which fully reproduces complex working environments such as upstream wake sweep, radial pressure gradient, wake sweep frequency, turbulence intensity, turbulence scale, incoming flow Reynolds number and the like in a real low-pressure turbine by respectively utilizing a rotary cylindrical rod and an annular blade grid, changing the rotating speed of a motor and the distance between spokes, adjusting the wire diameter size, the distance and the mounting position of a turbulence grid and adjusting the frequency of a frequency converter of a centrifugal fan, and has convenient and controllable flow field parameters, and is easy to realize the refined flow field measurement in the low-pressure turbine.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a low-pressure turbine annular cascade test bed with unsteady wake simulation function at least comprises a low-pressure turbine annular cascade and a turbine guide vane ring coaxially arranged at the upstream of the low-pressure turbine annular cascade, and is characterized in that,
turbulence grids are arranged above the turbine guide vane rings, and the turbulence intensity and the turbulence scale of the incoming flow are adjusted by adjusting the wire diameter size, the distance and the mounting position of the turbulence grids;
the test bed also comprises a cylindrical rod turntable and a plurality of cylindrical rods which are uniformly arranged on the edge of the cylindrical rod turntable along the circumferential direction, the cylindrical rod turntable is coaxially arranged between the turbine guide vane ring and the low-pressure turbine annular blade cascade and is arranged close to the low-pressure turbine annular blade cascade, a plurality of cylindrical rod mounting holes which extend along the radial direction are uniformly arranged on the edge of the cylindrical rod turntable along the circumferential direction, and each cylindrical rod is arranged in each cylindrical rod mounting hole in a number-adjustable manner; a rotating shaft is fixedly arranged at the center of the cylindrical rod turntable and is in transmission connection with an external power source;
an axial inflow air source is arranged at the upstream of the turbine guide vane ring.
Preferably, the mounting angle of each turbine vane on the turbine vane ring is adjustable to provide a suitable inlet airflow angle for the low pressure turbine annular cascade.
Preferably, the axial inflow air source is generated by an alternating current variable frequency centrifugal fan.
Preferably, the cylindrical rod turntable is a solid turntable, and the cylindrical rod mounting holes are arranged at equal angles along the circumferential direction so as to ensure good dynamic balance.
Preferably, each of the cylindrical rod mounting holes is a threaded hole, a mounting bolt is correspondingly arranged in each of the threaded holes, a central through hole extending along the axial direction of each mounting bolt is arranged in the center of each mounting bolt, a spoke cap is arranged at the bottom end of each cylindrical rod, and the free end of each cylindrical rod is fixedly arranged between the mounting bolt and the threaded hole by virtue of the spoke cap at the bottom of the cylindrical rod after passing through the central through hole of the corresponding mounting bolt.
Preferably, the installation number of the cylindrical rods is adjustable so as to adjust the distance between the spokes, thereby controlling the flow coefficient.
Preferably, the external power source is a variable frequency motor, and the rotating shaft fixedly arranged on the cylindrical rod turntable is in transmission connection with the variable frequency motor.
Furthermore, the rotating speed of the variable frequency motor is adjustable, so that the rotating speed of the cylindrical rod turntable and the cylindrical rod is controlled, and the sweep frequency of the tail trace is controlled.
Preferably, the rotating direction of the cylindrical rod rotating disk is from the suction surface to the pressure surface of the low-pressure turbine annular blade cascade, and the upstream airflow forms an upstream periodic unsteady wake under the disturbance of each cylindrical rod.
Preferably, the axial distance between the cylindrical rod rotating disc and the low-pressure turbine annular blade cascade is adjustable, so that different positions of an upstream wake on a suction surface of a turbine blade are changed, and the separation of the suction surface of the blade and the secondary flow intensity of an end area are better controlled.
Compared with the prior art, the low-pressure turbine annular cascade test bed with the unsteady wake simulation function has the remarkable technical effects that:
(1) according to the invention, complex working environments such as upstream wake sweep, radial pressure gradient, wake sweep frequency, turbulence intensity and turbulence scale, incoming flow Reynolds number and the like in a real low-pressure turbine are fully reproduced by respectively rotating the cylindrical rod and the annular cascade, changing the rotating speed of the motor and the distance between spokes, adjusting the wire diameter size, the distance and the mounting position of a turbulence grid and adjusting the frequency of a frequency converter of a centrifugal fan, and flow parameters of a flow field are convenient and controllable, so that the internal refined flow field measurement of the low-pressure turbine is easily realized;
(2) the low-pressure turbine annular cascade test bed with the unsteady wake simulation function has the advantages of simple structure, convenience in processing and easiness in implementation, can fully simulate the unsteady wake inside the real low-pressure turbine and the radial pressure gradient caused by the annular curvature of the wall surface, and can accurately restore the flow state inside the low-pressure turbine;
(3) in the low-pressure turbine annular cascade test bed with the unsteady wake simulation function, the inlet airflow angle of the low-pressure turbine annular cascade is adjusted by utilizing an upstream turbine guide vane ring, the unsteady effect of the annular cascade upstream wake is simulated by utilizing a rotating cylindrical rod, and the radial pressure gradient in the real low-pressure turbine is reduced by utilizing the annular cascade;
(4) in the low-pressure turbine annular cascade test bed with the unsteady wake simulation function, the sweeping frequency and the flow coefficient of the upstream wake of the annular cascade are adjusted by adjusting the rotating speed of a motor and the number of cylindrical rods; the rotating shaft of the cylindrical rod rotating disc and the turbine hub casing are concentrically arranged, so that high-speed rotation of the cylindrical rod is easy to realize, and the real wake sweeping frequency in the low-pressure turbine is truly reproduced.
Drawings
FIG. 1 is a schematic view of a low pressure turbine annular cascade test bed with unsteady wake simulation of the present invention;
FIG. 2 is a schematic diagram of an annular turbulence grid, wherein (A) is a schematic diagram of an overall grid and (B) is a partially enlarged schematic diagram;
FIG. 3 is a schematic view of a cylindrical rod;
FIG. 4 is a two-dimensional view of a bolt;
FIG. 5 is a schematic view of the installation of the cylindrical rod on the turntable, wherein (A) is a schematic view of the whole installation, and (B) is a schematic view of the cylindrical rod, the bolt and the turntable assembly which is partially enlarged;
in the figure, an axial inflow air source 1, an annular turbulence grid 2, a turbine guide vane ring 3, a cylindrical rod 4, a cylindrical rod turntable 5, a low-pressure turbine annular vane cascade 6, an outer culvert casing 7, an inner culvert hub 8, a rotating shaft 9, an external power source 10 and a mounting bolt 11.
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.
As shown in fig. 1, in order to simulate unsteady characteristics in an impeller mechanical stage environment, the low-pressure turbine annular cascade test bed with unsteady wake simulation function of the present invention simulates blade wake characteristics by using the rotation of a cylindrical rod, and comprises a low-pressure turbine annular cascade 6, a turbine guide vane ring 3 coaxially disposed at the upstream of the low-pressure turbine annular cascade 6, and a cylindrical rod turntable 5 coaxially disposed between the turbine guide vane ring 3 and the low-pressure turbine annular cascade 6 and disposed adjacent to the low-pressure turbine annular cascade 6, wherein the edge of the cylindrical rod turntable 5 is uniformly provided with a plurality of cylindrical rod mounting holes extending along the radial direction along the circumferential direction thereof, and each cylindrical rod 4 is uniformly mounted in each cylindrical rod mounting hole in a number-adjustable manner in the circumferential direction; a rotating shaft 9 is fixedly arranged at the center of the cylindrical rod turntable 5, and the rotating shaft 9 is connected with an external power source 10 through a coupler; an annular turbulence grid 2 is arranged at the upstream of the turbine guide vane ring 3, and an axial inflow air source 1 is arranged at the upstream of the annular turbulence grid 2.
The invention relates to a low-pressure turbine annular cascade test bed with an unsteady wake simulation function, which mainly comprises an axial inflow air source 1 generated by an alternating-current variable-frequency centrifugal fan, wherein a cylindrical rod 4 is mainly used for simulating the periodic wake of an upstream movable blade, and a turbine guide vane ring 3 is mainly used for providing a proper inlet airflow angle for a low-pressure turbine annular cascade 6. The cylinder stick 4 is installed on cylinder stick carousel 5, and cylinder stick carousel 5 passes through bolt fixed connection with pivot 9 to with the outer culvert casket 7 and the culvert wheel hub 8 of low pressure turbine annular cascade 6 concentric, external power source 10 is preferably inverter motor, and passes through the coupling joint with pivot 9.
An annular turbulence grid 2 is arranged above the turbine guide vane ring 3, and the incoming flow turbulence intensity and the turbulence scale can be adjusted by adjusting the wire diameter size and the distance t of the turbulence grid 2 and the installation distance from the annular guide vane ring 3, as shown in fig. 2. One end of the cylindrical rod 4 is provided with a spoke cap, and the other end is smooth and has no bulge, as shown in figure 3. 60 threaded holes are uniformly processed on the rotary disc 5 along the circumference, firstly, a central through hole extending along the axial direction of the mounting bolt 11 is processed at the central position of the mounting bolt, as shown in figure 4, then, the smooth end of the cylindrical rod 4 is inserted into the central through hole of the mounting bolt 10, and then, the mounting bolt 11 is screwed into the threaded hole on the rotary disc 5 of the cylindrical rod, and the bottom end of the threaded hole just props up the spoke cap, as shown in figure 5. The rotation speed of the cylindrical rod 4 can be controlled by adjusting the rotation speed of the external power source 10, and the spoke spacing can be adjusted by adjusting the number of the cylindrical rods 4 on the cylindrical rod turntable 5, so that the flow coefficient and the tail sweep frequency can be controlled. The method can fully simulate the unsteady wake and the radial pressure gradient in the real low-pressure turbine, and has the advantages of convenient operation and easy processing. The rotating direction of the cylindrical rod rotating disk 5 is from the suction surface to the pressure surface of the low-pressure turbine annular blade cascade 6, and the upstream airflow forms an upstream periodic unsteady wake under the disturbance of each cylindrical rod 4. The axial distance between the cylindrical rod rotating disc 5 and the low-pressure turbine annular blade cascade 6 is adjustable, so that different positions of an upstream wake on a suction surface of a turbine blade are changed, and the separation of the suction surface of the blade and the secondary flow intensity of an end area are controlled better.
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 (10)
1. A low-pressure turbine annular cascade test bed with unsteady wake simulation function at least comprises a low-pressure turbine annular cascade and a turbine guide vane ring coaxially arranged at the upstream of the low-pressure turbine annular cascade, and is characterized in that,
turbulence grids are arranged above the turbine guide vane rings, and the turbulence intensity and the turbulence scale of the incoming flow are adjusted by adjusting the wire diameter size, the distance and the mounting position of the turbulence grids;
the test bed also comprises a cylindrical rod turntable and a plurality of cylindrical rods which are uniformly arranged on the edge of the cylindrical rod turntable along the circumferential direction, the cylindrical rod turntable is coaxially arranged between the turbine guide vane ring and the low-pressure turbine annular blade cascade and is arranged close to the low-pressure turbine annular blade cascade, a plurality of cylindrical rod mounting holes which extend along the radial direction are uniformly arranged on the edge of the cylindrical rod turntable along the circumferential direction, and each cylindrical rod is arranged in each cylindrical rod mounting hole in a number-adjustable manner; a rotating shaft is fixedly arranged at the center of the cylindrical rod turntable and is in transmission connection with an external power source;
an axial inflow air source is arranged at the upstream of the turbine guide vane ring.
2. The test rig of the preceding claim, wherein the setting angle of each turbine vane on the turbine vane ring is adjustable to provide a suitable inlet airflow angle for the low pressure turbine annular cascade.
3. Test bench according to the preceding claim, characterized in that the axial incoming air source is generated by an ac variable frequency centrifugal fan.
4. The test bed according to the preceding claim, wherein the cylindrical rod turntable is a solid turntable, and the cylindrical rod mounting holes are arranged at equal angles along the circumferential direction so as to ensure good dynamic balance.
5. The test bed as claimed in the preceding claim, wherein each of the cylindrical rod mounting holes is a threaded hole, a corresponding mounting bolt is disposed in each of the threaded holes, a central through hole extending in an axial direction of each of the mounting bolts is disposed in a center of each of the mounting bolts, a spoke cap is disposed at a bottom end of each of the cylindrical rods, and a free end of each of the cylindrical rods is fixedly disposed between the mounting bolt and the threaded hole by means of the spoke cap at the bottom end of each of the cylindrical rods after passing through the central through hole of the corresponding mounting bolt.
6. Test bench according to the preceding claim, characterized in that the number of installed cylindrical bars is adjustable to adjust the spoke spacing and thereby control the flow coefficient.
7. The test bench of the previous claim, wherein the external power source is a variable frequency motor, and the rotating shaft fixedly arranged on the cylindrical bar turntable is in transmission connection with the variable frequency motor.
8. The test bench of claim 7, wherein the rotation speed of the variable frequency motor is adjustable so as to control the rotation speed of the cylindrical rod turntable and the cylindrical rod, and then control the trailing sweep frequency.
9. The test bench of the previous claim, wherein the rotation direction of the cylindrical rod rotating disk is from the suction surface to the pressure surface of the low-pressure turbine annular blade cascade, and the upstream airflow forms an upstream periodic unsteady wake under the disturbance of each cylindrical rod.
10. The test rig of the preceding claim, wherein the axial distance between the cylindrical rod rotor disk and the low pressure turbine annular cascade is adjustable to vary the different positions of the upstream wake impinging on the turbine blade suction surface to better control blade suction surface separation and tip area secondary flow intensity.
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Cited By (3)
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| CN114396314A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Supersonic speed axial flow composite bladeless turbine |
| CN114689329A (en) * | 2022-05-09 | 2022-07-01 | 北京航空航天大学 | Annular cascade test bench and aeroelasticity test system thereof |
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