CN112577755A - Turbine hub sealing experimental device considering upstream unsteady effect - Google Patents
Turbine hub sealing experimental device considering upstream unsteady effect Download PDFInfo
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- 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
- G01M15/00—Testing of 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
Abstract
The invention discloses a turbine hub sealing experimental device considering upstream unsteady effect, which is used for simulating the interaction characteristics of sealing flow and main flow in the mechanical environment of an impeller, obtaining the circumferential speed of hub sealing flow by utilizing high-speed rotation of a disc, adjusting the airflow angle of an inlet of an annular blade cascade by utilizing an upstream guide vane, simulating the unsteady effect of an upstream wake of the annular blade cascade by utilizing a rotating cylindrical rod, reducing the sealing flow in a real turbine by utilizing the rotation of a disc cavity wall, and installing different disc cavity wall structures, the influence of different sealing cavities on the flow at the turbine end area is very conveniently researched on the premise of considering the upstream unsteady effect, and can conveniently change different seal cavity structures and study the interact of seal outflow and turbine mainstream, obtain more accurate three-dimensional unsteady flow field structure easily, can save the experiment cost again, reduce the measurement degree of difficulty.
Description
Technical Field
The invention belongs to the field of unsteady experiments of turbine components of aero-engines/gas turbines, relates to a turbine hub sealing experiment device, and particularly relates to a low-speed large-size annular turbine hub sealing experiment device considering an upstream unsteady effect. Because the cylindrical rod is similar to the wake flow field structure of the downstream of the blade, the wake of the upstream blade is simulated by using the cylindrical rod widely, and in addition, the sealing outflow in the real engine is a complex rotary flow and has larger axial, radial and circumferential speeds. The invention respectively utilizes the rotary cylindrical rod, the annular sealing cavity and the annular turbine blade to simulate complex flow field environments such as real turbine-grade internal upstream unsteady effect, interference phenomenon of sealing flow and main flow and the like, and flow field parameters are convenient and controllable, and the internal refined flow field measurement of the turbine is easy to realize.
Background
The turbine is one of the core components of an aircraft engine/gas turbine, while the high pressure turbine is more important as a core component. In order to ensure the reliable operation of the turbine rotor and avoid the scratch between the rotating and static blade rows, a disc cavity is arranged between the turbine rotor blade row and the stator blade row. When the engine runs, due to the fact that pressure difference exists between the main flow and the disk cavity, high-temperature main flow combustion gas can invade the disk cavity to cause overheating of the turbine disk. In addition, turbine inlet temperatures are constantly being increased in pursuit of higher engine power, efficiency and thrust-weight ratio, which must be cooled in order to ensure safe and reliable operation of the turbine disk. Therefore, cold air introduced by a compressor stage is generally introduced into the disk cavity to serve as hub sealing airflow to improve the pressure in the disk cavity and prevent high-temperature main flow gas from invading, and meanwhile, the cold air can cool the roots of the turbine disk and the movable blades. However, since the sealing flow can perform a complex interaction with the main flow in the turbine passage while ensuring the normal operation of the engine, two air flows with different characteristics are mixed, the flow loss is increased, and the turbine performance is further increased. Therefore, the design of the turbine hub sealing structure is to reduce the air quantity of the air supply of the disc cavity as much as possible and improve the engine efficiency on the premise of ensuring that the working temperature of the hub is within the material bearing range, and more researchers pay more and more attention to the research on the mixing mechanism of the hub sealing flow and the main flow of the channel and the corresponding loss transport mechanism, especially under the unsteady environment between the turbine stages.
In consideration of the fact that the cost for measuring the parameters of the flow field in the turbine is high in the high-temperature, high-pressure and high-speed environments of the real engine, the internal space of the real turbine is relatively narrow, the measuring environment is severe, the accurate measurement of the parameters of the complex flow field in the end region of the hub is quite difficult, and the abundant and continuous space-time flow field information in the turbine stage is difficult to obtain. Therefore, it is necessary to design a new experimental platform to reproduce complex flow field environments such as upstream unsteady effects, interference phenomena between the sealed flow and the main flow, and the like inside the real turbine stage. Compared with the prior art, the low-speed large-size annular turbine hub sealing experiment table designed by the invention can realize high-speed rotation of the turbine disc, is convenient to replace different sealing cavity structures to research the interaction between the sealing outflow and the turbine main flow, is easy to obtain a more accurate three-dimensional unsteady flow field structure, can save the experiment cost and reduce the measurement difficulty.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention aims to provide a turbine hub sealing experimental device for considering the upstream unsteady effect, which can realize high-speed rotation of a turbine disc, is convenient for replacing different sealing cavity structures to research the interaction between a sealing outflow and a turbine main flow, is easy to obtain a more accurate three-dimensional unsteady flow field structure, can save the experimental cost and reduce the measurement difficulty.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a turbine hub sealing experimental device considering upstream unsteady effect comprises a fixedly arranged culvert casing and a culvert casing coaxially arranged in the culvert casing, wherein an annular space between the culvert casing and the culvert casing forms a main flow channel,
the outer culvert casing comprises a cylindrical outer culvert main body section and an outer culvert contraction section, wherein the cylindrical outer culvert main body section and the outer culvert contraction section are fixedly connected or form an integral structure, the cylindrical outer culvert main body section is fixedly arranged, the outer culvert contraction section is arranged at the upstream of the cylindrical outer culvert main body section, a main flow gas source is arranged outside the outer culvert contraction section, and the main flow gas source is used for introducing main flow gas parallel to the axis of the outer culvert contraction section;
the culvert casing comprises a culvert air inlet cone, a first cylindrical culvert main body section and a second cylindrical culvert main body section which are sequentially arranged along the axial direction, wherein the culvert air inlet cone is fixedly connected with the first cylindrical culvert main body section or forms an integral structure, the front end of the first cylindrical culvert main body section is basically flush with the front end of the cylindrical culvert main body section in the axial direction, the rear end of the second cylindrical culvert main body section is basically flush with the rear end of the cylindrical culvert main body section in the axial direction, and the rear end of the first cylindrical culvert main body section and the front end of the second cylindrical culvert main body section are axially spaced to form an annular slit between the first cylindrical culvert main body section and the second cylindrical culvert main body section,
the front end of the first cylindrical inner culvert main body segment is formed into a runner inlet of the main runner channel, the rear end of the second cylindrical inner culvert main body segment is formed into a runner outlet of the main runner channel, a plurality of inlet support plates which extend along the radial direction and are uniformly distributed along the circumferential direction are arranged near the runner inlet, a plurality of outlet support plates which extend along the radial direction and are uniformly distributed along the circumferential direction are arranged near the runner outlet, one end of each inlet support plate is fixedly connected with the outer wall of the front end of the first cylindrical inner culvert main body segment, the other end of each inlet support plate is fixedly connected with the inner wall of the front end of the cylindrical outer culvert main body segment, one end of each outlet support plate is fixedly connected with the outer wall of the rear end of the second cylindrical inner culvert main body segment, and the other end of each outlet support plate is,
the outer wall of the first cylindrical inner main body section is provided with a circle of turbine guide vanes which are uniformly distributed along the circumferential direction and are positioned at the downstream of the inlet support plate in the axial direction, the other end of each turbine guide vane is fixedly connected with the inner wall of the cylindrical outer main body section, the outer wall of the front end of the second cylindrical inner main body section is provided with a circle of turbine blades which are uniformly distributed along the circumferential direction, the other end of each turbine blade is fixedly connected with the inner wall of the cylindrical outer main body section,
a power source is fixedly arranged in the first cylindrical containing main body section, a power output end of the power source is in transmission connection with a rotary table which is coaxially arranged with the first cylindrical containing main body section, the rotary table is axially arranged in the annular slit, the diameter of the rotary table is at least equal to the outer diameter of the first cylindrical containing main body section, a plurality of rotary cylindrical rods which are uniformly distributed along the circumferential direction and radially extend into the main flow channel are fixedly arranged on the side wall of the rotary table, and a disc-shaped first disc cavity end wall with the shape and the size matched with the rotary table is fixedly arranged on the outer end face of the rotary table, which is opposite to the second cylindrical containing main body section;
a cylindrical tight-sealing cold air cavity which is coaxially arranged with the second cylindrical internal culvert main body section is fixedly arranged in the second cylindrical internal culvert main body section, the rear end of the cylindrical tight-sealing cold air cavity is communicated with a high-pressure tight-sealing cold air source, an annular second disc cavity end wall is fixedly arranged at the opening at the front end of the cylindrical tight-sealing cold air cavity, the outer diameter of the second disc cavity end wall is equivalent to that of the second cylindrical internal culvert main body section, the outer edge of the second disc cavity end wall is fixedly arranged on the wall surface near the front end of the second cylindrical internal culvert main body section,
an axial gap is formed between the end wall of the first disc cavity and the end wall of the second disc cavity, an annular sealing cavity is formed between the opposite end faces of the first disc cavity and the second disc cavity, and fish mouth sealing structures which are matched with each other are machined on the radial outer edges of the opposite end faces of the first disc cavity and the second disc cavity in the circumferential direction.
Preferably, the outer wall of the cylindrical culvert main body section is fixedly arranged on a base support frame.
Preferably, the main air source is an alternating-current variable-frequency centrifugal fan.
Preferably, an annular turbulence grid is arranged at the inlet of the runner, and the turbulence grid is positioned axially upstream of the inlet support plate and is used for improving the turbulence of the incoming flow of the inlet.
Preferably, the profiles of the inlet support plate and the outlet support plate are formed by stacking symmetrical wing sections, and the chord lines of the symmetrical wing sections are consistent with the axis of the main flow channel, so that the inlet support plate and the outlet support plate can play a strong supporting role and can ensure the minimum flow loss.
Preferably, the power source passes through the fixed setting of support and is in the first cylindrical containing main body section, the power take off end of power source pass through the shaft coupling with the carousel transmission is connected, just the power take off end of power source, shaft coupling, carousel with the coaxial mode of first cylindrical containing main body section is arranged.
Preferably, the first disk cavity end wall is fixedly arranged on the outer end face of the rotating disk through a fastener, and the second disk cavity end wall is fixedly arranged on the wall face near the front end of the second cylindrical containing main body section through a fastener.
Preferably, the radial outer edge of the outer end face of the first disc cavity end wall is provided with a circumferential ring groove, the radial outer edge of the outer end face of the second disc cavity end wall is provided with an annular protrusion, the annular protrusion extends into the circumferential ring groove, and the two are mutually matched to form the fish mouth sealing structure.
Preferably, an air inlet cover is arranged at the center of the end wall of the first disk cavity, the air inlet cover is a flow guide protrusion which is formed at the center of the end wall of the first disk cavity and extends into the cylindrical sealed cold air cavity along the axial direction, the air inlet cover is mainly used for reducing the flow loss of the sealed cold air, and the design can realize that the high-pressure sealed cold air smoothly reaches the sealed cavity through the cold air cavity.
Preferably, the cylindrical strictly-sealed cold air cavity is coaxially and fixedly arranged in the second cylindrical internal containing main body section through a bracket.
Preferably, a flow guide honeycomb is fixedly arranged in the cylindrical sealed cold air cavity and close to the rear end of the cylindrical sealed cold air cavity, and the flow guide honeycomb is used for improving the flow uniformity of the high-pressure sealed cold air.
Preferably, the high-pressure sealed cold air source is communicated with the cylindrical sealed cold air cavity through an expansion section, a large opening end of the expansion section is fixedly connected with the rear end of the cylindrical sealed cold air cavity, and a small opening end of the expansion section is communicated with the high-pressure sealed cold air source through a pipeline.
Furthermore, at least one flowmeter is arranged on the pipeline at the small opening end of the expansion section.
The invention relates to a turbine hub sealing experimental device considering upstream unsteady effect, which has the working principle that: in order to simulate the interaction characteristics of the sealing flow and the main flow in the mechanical environment of the impeller, the circumferential speed of the hub sealing flow is obtained by utilizing the high-speed rotation of the disc, the main flow gas enters a main flow channel after being accelerated by the outer culvert contraction section and the inner culvert air inlet cone, the airflow angle is deflected after the horizontal incoming flow passes through the turbine guide vane, so that a proper inlet airflow angle is provided for the downstream turbine blade, and the main function of the rotating cylindrical rod is to simulate the periodic wake of the upstream turbine blade. Rotatory cylinder stick is installed on the carousel, and the carousel is connected with external power source, is the chamber of obturating between cylinder stick and turbine blade row, and the structure in chamber of obturating mainly is set the chamber wall by first dish chamber end wall and second and decides, and this kind of design can guarantee that the power source drives cylinder stick and first dish chamber wall rotation to it has circumferential speed to make the chamber of obturating export air conditioning. The high-pressure sealed cold air source is communicated with the sealed cold air cavity. The method can fully simulate the unsteady effect and the interference effect of the seal flow and the main flow in the real turbine, and has the advantages of convenient operation and easy processing.
Compared with the prior art, the turbine hub sealing experimental device considering the upstream unsteady effect has the main technical effects that: (1) in order to simulate the interaction characteristics of the sealing flow and the main flow in the mechanical environment of the impeller, the high-speed rotation of the disc is used for obtaining the circumferential speed of the hub sealing flow, different sealing cavity structures are conveniently replaced to research the interaction of the sealing flow and the turbine main flow, a more accurate three-dimensional unsteady flow field structure is easily obtained, the experiment cost can be saved, and the measurement difficulty is reduced. (2) The turbine hub sealing experimental device is compact in structure and reasonable in arrangement of all parts, the upstream guide vanes are used for adjusting the airflow angle of the inlet of the annular blade cascade, the rotating cylindrical rod is used for simulating the unsteady effect of the upstream wake of the annular blade cascade, and the wall of the disk cavity is used for rotating to restore the sealing outflow in the real turbine. (3) The influence of different sealing cavities on the flow of the turbine end region can be conveniently researched by installing different disk cavity wall structures on the premise of considering the upstream unsteady effect. (4) The inlet and outlet support plate wing type design can guarantee that the effect of supporting the containing casing is achieved, and meanwhile, the flow loss is small. (5) The use of the connotative air inlet cone and the sealed cold air inlet hood can meet the requirements of lower flow resistance and small pneumatic loss.
Drawings
FIG. 1 is a schematic structural diagram of a turbine hub seal experimental apparatus taking upstream unsteady effects into consideration according to the present invention;
FIG. 2 is a partially enlarged schematic view of a sealing chamber according to the present invention;
FIG. 3 is a schematic view of the turbine vane, rotating cylindrical bar and turbine blade installation of the present invention;
FIG. 4 is a schematic view of an airfoil of an inlet plate and an outlet plate in the present invention, wherein (A) is an inlet plate airfoil, and (B) is an outlet plate airfoil.
Description of reference numerals:
mainstream air supply 1, outer culvert shrink section 2, culvert inlet cone 3, torrent net 4, turbine stator 5, rotatory cylinder stick 6, the chamber of obturating 7, turbine blade 8, culvert casing 9, high-pressure air conditioning source of obturating 10, flowmeter 11, expansion section 12, honeycomb 13, the chamber of obturating 14, admit air cover 15, carousel 16, first dish chamber endwall 17, second dish chamber wall 18, power supply 19, shaft coupling 20, support frame 21, import extension board 22, export extension board 23, base support frame 24, bolt 25, bolt 26.
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 to 4, the turbine hub sealing experimental apparatus considering the upstream unsteady effect of the present invention includes a fixedly disposed bypass casing, and a bypass casing 9 coaxially disposed in the bypass casing, wherein an annular space between the bypass casing and the bypass casing 9 forms a main flow channel. Wherein, the outer box of containing includes a tube-shape outer containing main part section and an outer containing shrinkage section 2, and tube-shape outer containing main part section and outer containing shrinkage section 2 fixed connection or form structure as an organic whole, and tube-shape outer containing main part section is fixed to be set up, and outer containing shrinkage section 2 sets up the upper reaches at tube-shape outer containing main part section, and the outside of outer containing shrinkage section sets up mainstream air supply 1, and mainstream air supply 1 is used for outwards containing the shrinkage section and lets in the mainstream gas parallel rather than the axis. The culvert casing 9 comprises a culvert air inlet cone 3, a first cylindrical culvert main body section and a second cylindrical culvert main body section, wherein the culvert air inlet cone 3 and the first cylindrical culvert main body section are sequentially arranged along the axial direction, the culvert air inlet cone 3 and the first cylindrical culvert main body section are fixedly connected or form an integrated structure, the front end of the first cylindrical culvert main body section is basically flush with the front end of the cylindrical culvert main body section in the axial direction, the rear end of the second cylindrical culvert main body section is basically flush with the rear end of the cylindrical culvert main body section in the axial direction, and the rear end of the first cylindrical culvert main body section and the front end of the second cylindrical culvert main body section are axially spaced to form an annular slit between the first cylindrical culvert main body section and the second cylindrical culvert main body section. The front end of the first cylindrical internal main body section is formed into a flow channel inlet of a main flow channel, the rear end of the second cylindrical internal main body section is formed into a flow channel outlet of the main flow channel, a plurality of inlet support plates 22 which radially extend and are uniformly distributed along the circumferential direction are arranged at positions close to the flow channel inlet, a plurality of outlet support plates 23 which radially extend and are uniformly distributed along the circumferential direction are arranged at positions close to the flow channel outlet, one end of each inlet support plate 22 is fixedly connected with the outer wall of the front end of the first cylindrical internal main body section, the other end of each inlet support plate 22 is fixedly connected with the inner wall of the front end of the cylindrical external main body section, one end of each outlet support plate 23 is fixedly connected with the outer wall of the rear end of the second cylindrical internal main body section, and. The outer wall of the first cylindrical internal containing main body section is provided with a circle of turbine guide vanes 5 which are uniformly distributed along the circumferential direction and are positioned at the downstream of the inlet support plate 22 in the axial direction, the other end of each turbine guide vane 5 is fixedly connected with the inner wall of the cylindrical external containing main body section, the outer wall of the front end of the second cylindrical internal containing main body section is provided with a circle of turbine blades 8 which are uniformly distributed along the circumferential direction, and the other end of each turbine blade 8 is fixedly connected with the inner wall of the cylindrical external containing main body section. A power source 19 is fixedly arranged in the first cylindrical containing main body section, a power output end of the power source 19 is in transmission connection with a rotary table 16 which is coaxially arranged with the first cylindrical containing main body section, the rotary table 16 is axially arranged in the annular slit, the diameter of the rotary table 16 is at least equal to the outer diameter of the first cylindrical containing main body section, a plurality of rotary cylindrical rods 6 which are uniformly distributed along the circumferential direction and radially extend into the main flow channel are fixedly arranged on the side wall of the rotary table 16, and a disc-shaped first disc cavity end wall 17 with the shape and the size matched with the rotary table 16 is fixedly arranged on the outer end face of the rotary table 16, which is opposite to the second cylindrical containing main body section; the second cylindrical internal culvert main body section is internally and fixedly provided with a cylindrical cold air cavity 14 which is coaxially arranged with the second cylindrical internal culvert main body section, the rear end of the cylindrical cold air cavity 14 is communicated with a high-pressure sealed cold air source 10, the front end opening of the cylindrical cold air cavity 14 is fixedly provided with an annular second disc cavity end wall 18, the outer diameter of the second disc cavity end wall 18 is equivalent to that of the second cylindrical internal culvert main body section, and the outer edge of the second disc cavity end wall 18 is fixedly arranged on the wall surface near the front end of the second cylindrical internal culvert main body section. An axial gap is formed between the first disc cavity end wall 17 and the second disc cavity end wall 18, an annular sealing cavity 7 is formed between the opposite end faces, and fish mouth sealing structures which are matched with each other are machined at the radial outer edges of the opposite end faces along the circumferential direction.
More specifically, as shown in fig. 1-4, the outer wall of the cylindrical culvert body section is fixedly disposed on a base support frame 24. The main air source is an alternating current variable frequency centrifugal fan. An annular turbulence grid 4 is arranged at the inlet of the flow channel, and the turbulence grid 4 is axially positioned at the upstream of the inlet support plate 22, and the turbulence grid 4 is used for improving the turbulence of the incoming flow at the inlet. The profiles of the inlet support plate 22 and the outlet support plate 23 are formed by stacking symmetrical wing profiles, and the chord lines of the symmetrical wing profiles are consistent with the axis of the main flow channel, so that the inlet support plate 22 and the outlet support plate 23 can play a strong supporting role and can ensure the minimum flow loss. Power supply 19 passes through annular support frame 21 and fixes the setting in first cylindrical containing main body segment, and power output of power supply 19 passes through shaft coupling 20 and is connected with the transmission of carousel 16, and power output, shaft coupling 20, the carousel 16 of power supply 19 arrange with the coaxial mode of first cylindrical containing main body segment. The first disk chamber end wall 17 is fixedly arranged on the outer end face of the rotary disk 16 by fasteners, and the second disk chamber end wall 18 is fixedly arranged on the wall face near the front end of the second cylindrical containing body section by fasteners. The radial outer edge of the outer end face of the first disc cavity end wall 17 is provided with a circumferential ring groove, the radial outer edge of the outer end face of the second disc cavity end wall 18 is provided with an annular bulge, the annular bulge extends into the circumferential ring groove, and the annular bulge and the circumferential ring groove are matched with each other to form a fish mouth sealing structure. An air inlet cover 15 is arranged at the center of the first disc cavity end wall 17, the air inlet cover 15 is a flow guide protrusion which is formed at the center of the first disc cavity end wall 17 and extends into the cylindrical cold air cavity 14 along the axial direction, the air inlet cover 15 mainly has the function of reducing the flow loss of sealed cold air, and the design can realize that high-pressure sealed cold air smoothly reaches the sealed cavity 7 through the cold air cavity 14.
The cylindrical cold air cavity 14 is coaxially and fixedly arranged in the second cylindrical culvert main body section through a bracket. A flow guide honeycomb 13 is fixedly arranged in the cylindrical cold air cavity 14 and close to the rear end of the cylindrical cold air cavity, and the flow guide honeycomb 13 is used for improving the flowing uniformity of high-pressure sealed cold air. The high-pressure sealed cold air source 10 is communicated with the cylindrical cold air chamber 14 through an expansion section 12, the large opening end of the expansion section 10 is fixedly connected with the rear end of the cylindrical cold air chamber 14, and the small opening end is communicated with the high-pressure sealed cold air source 10 through a pipeline. At least one flowmeter 11 is arranged on the pipeline at the small-opening end of the expanding section 10.
In order to simulate the interaction characteristics of the sealing flow and the main flow in the mechanical environment of the impeller, the circumferential speed of the hub sealing flow is obtained by utilizing the high-speed rotation of the disc, the main flow source 1 is mainly generated by an alternating-current variable-frequency centrifugal fan, the air flow passes through a runner inlet turbulence grid 4 after being accelerated by an outer culvert contraction section 2 and an inner culvert air inlet cone 3, and the turbulence grid mainly has the function of improving the turbulence degree of inlet incoming flow. The flow angle is deflected horizontally after passing through the turbine vanes 5 to provide the appropriate inlet flow angle to the annular turbine blades 8, as shown in FIG. 3, and the primary function of the rotating cylindrical rods 6 is to simulate the periodic wake of the upstream turbine blades. Rotatory cylinder stick 6 is installed on carousel 16, and carousel 16 passes through shaft coupling 20 to be connected with external power source 19, and external power source 19 installs on annular bracing frame 21, will guarantee during the installation that shaft coupling 20, annular bracing frame 21 and connotation machine casket 9 three are concentric. Between the cylindrical rod 6 and the turbine blade 8 is a sealing chamber 7, the structure of which is mainly determined by a first chamber end wall 17 and a second chamber wall 18, and the first chamber end wall 17 is connected with the rotary disc 16 by bolts 25, and the second chamber wall 18 is connected with the connotation casing 9 by bolts 26. The design can ensure that the power source 19 drives the cylindrical rod 6 and the left disc cavity wall 17 to rotate, so that the cold air at the outlet of the sealing cavity 7 has circumferential speed. The high-pressure sealed cold air source 10 enters the expansion section 12 through the flowmeter 11 and enters the cold air cavity 14, the honeycomb 13 mainly functions to improve the flow uniformity of sealed cold air, the air inlet cover 15 mainly functions to reduce the flow loss of the sealed cold air, and the design can realize that the high-pressure sealed cold air 10 smoothly reaches the sealed cavity 7 through the cold air cavity 14. The power source 19 and the whole cooling air cavity 14 are embedded inside the culvert casing 9, the culvert casing 9 is connected with the base support frame 24 through 3 inlet support plates 22 and 3 outlet support plates 23 which are uniformly distributed according to the circumference, wherein the inlet support plates 22 and the outlet support plates 23 are designed according to the NACA airfoil profile, so that the power source can play a strong supporting role and can ensure the minimum flow loss, as shown in FIG. 4. The method can fully simulate the unsteady effect and the interference effect of the seal flow and the main flow in the real turbine, and has the advantages of convenient operation and easy processing.
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 turbine hub sealing experimental device considering upstream unsteady effect comprises a fixedly arranged culvert casing and a culvert casing coaxially arranged in the culvert casing, wherein an annular space between the culvert casing and the culvert casing forms a main flow channel,
the outer culvert casing comprises a cylindrical outer culvert main body section and an outer culvert contraction section, wherein the cylindrical outer culvert main body section and the outer culvert contraction section are fixedly connected or form an integral structure, the cylindrical outer culvert main body section is fixedly arranged, the outer culvert contraction section is arranged at the upstream of the cylindrical outer culvert main body section, a main flow gas source is arranged outside the outer culvert contraction section, and the main flow gas source is used for introducing main flow gas parallel to the axis of the outer culvert contraction section;
the culvert casing comprises a culvert air inlet cone, a first cylindrical culvert main body section and a second cylindrical culvert main body section which are sequentially arranged along the axial direction, wherein the culvert air inlet cone is fixedly connected with the first cylindrical culvert main body section or forms an integral structure, the front end of the first cylindrical culvert main body section is basically flush with the front end of the cylindrical culvert main body section in the axial direction, the rear end of the second cylindrical culvert main body section is basically flush with the rear end of the cylindrical culvert main body section in the axial direction, and the rear end of the first cylindrical culvert main body section and the front end of the second cylindrical culvert main body section are axially spaced to form an annular slit between the first cylindrical culvert main body section and the second cylindrical culvert main body section,
the front end of the first cylindrical inner culvert main body segment is formed into a runner inlet of the main runner channel, the rear end of the second cylindrical inner culvert main body segment is formed into a runner outlet of the main runner channel, a plurality of inlet support plates which extend along the radial direction and are uniformly distributed along the circumferential direction are arranged near the runner inlet, a plurality of outlet support plates which extend along the radial direction and are uniformly distributed along the circumferential direction are arranged near the runner outlet, one end of each inlet support plate is fixedly connected with the outer wall of the front end of the first cylindrical inner culvert main body segment, the other end of each inlet support plate is fixedly connected with the inner wall of the front end of the cylindrical outer culvert main body segment, one end of each outlet support plate is fixedly connected with the outer wall of the rear end of the second cylindrical inner culvert main body segment, and the other end of each outlet support plate is,
the outer wall of the first cylindrical inner main body section is provided with a circle of turbine guide vanes which are uniformly distributed along the circumferential direction and are positioned at the downstream of the inlet support plate in the axial direction, the other end of each turbine guide vane is fixedly connected with the inner wall of the cylindrical outer main body section, the outer wall of the front end of the second cylindrical inner main body section is provided with a circle of turbine blades which are uniformly distributed along the circumferential direction, the other end of each turbine blade is fixedly connected with the inner wall of the cylindrical outer main body section,
a power source is fixedly arranged in the first cylindrical containing main body section, a power output end of the power source is in transmission connection with a rotary table which is coaxially arranged with the first cylindrical containing main body section, the rotary table is axially arranged in the annular slit, the diameter of the rotary table is at least equal to the outer diameter of the first cylindrical containing main body section, a plurality of rotary cylindrical rods which are uniformly distributed along the circumferential direction and radially extend into the main flow channel are fixedly arranged on the side wall of the rotary table, and a disc-shaped first disc cavity end wall with the shape and the size matched with the rotary table is fixedly arranged on the outer end face of the rotary table, which is opposite to the second cylindrical containing main body section;
a cylindrical tight-sealing cold air cavity which is coaxially arranged with the second cylindrical internal culvert main body section is fixedly arranged in the second cylindrical internal culvert main body section, the rear end of the cylindrical tight-sealing cold air cavity is communicated with a high-pressure tight-sealing cold air source, an annular second disc cavity end wall is fixedly arranged at the opening at the front end of the cylindrical tight-sealing cold air cavity, the outer diameter of the second disc cavity end wall is equivalent to that of the second cylindrical internal culvert main body section, the outer edge of the second disc cavity end wall is fixedly arranged on the wall surface near the front end of the second cylindrical internal culvert main body section,
an axial gap is formed between the end wall of the first disc cavity and the end wall of the second disc cavity, an annular sealing cavity is formed between the opposite end faces of the first disc cavity and the second disc cavity, and fish mouth sealing structures which are matched with each other are machined on the radial outer edges of the opposite end faces of the first disc cavity and the second disc cavity in the circumferential direction.
2. The turbine hub sealing experimental apparatus as claimed in the preceding claim, wherein the outer wall of the cylindrical culvert body section is fixedly arranged on a base support frame.
3. The turbine hub sealing experimental device according to the preceding claim, wherein the main air source is an alternating-current variable-frequency centrifugal fan.
4. The turbine hub seal test device of the previous claim, wherein an annular turbulence grid is disposed at the inlet of the flow channel, and the turbulence grid is located axially upstream of the inlet support plate, and the turbulence grid is configured to increase turbulence of the incoming flow.
5. The turbine hub sealing experimental device according to the preceding claim, wherein the profiles of the inlet and outlet support plates are stacked by symmetrical airfoils, and chord lines of the symmetrical airfoils are consistent with the axis of the main flow channel, so that the inlet and outlet support plates can play a strong supporting role and ensure the minimum flow loss.
6. The turbine hub sealing experimental device according to the preceding claim, wherein the power source is fixedly arranged in the first cylindrical containing main body section through a support, a power output end of the power source is in transmission connection with the rotary table through a coupler, and the power output end, the coupler and the rotary table of the power source are arranged in a coaxial manner with the first cylindrical containing main body section.
7. The turbine hub sealing test device of the previous claim, wherein the first disk cavity end wall is fixedly arranged on the outer end face of the disk through a fastener, and the second disk cavity end wall is fixedly arranged on the wall surface near the front end of the second cylindrical containing main body section through a fastener.
8. The turbine hub sealing test device of the preceding claim, wherein a circumferential ring groove is formed in a radially outer edge of the outer end surface of the first disk cavity end wall, an annular protrusion is formed in a radially outer edge of the outer end surface of the second disk cavity end wall, the annular protrusion extends into the circumferential ring groove, and the two are mutually matched to form the fish mouth sealing structure.
9. The turbine hub sealing experimental device of the previous claim, wherein an air inlet cover is disposed at the center of the end wall of the first disk cavity, the air inlet cover is a guide protrusion formed at the center of the end wall of the first disk cavity and extending into the cylindrical sealed cold air cavity along the axial direction, the main function of the air inlet cover is to reduce the flow loss of the sealed cold air, and this design can enable the high-pressure sealed cold air to smoothly reach the sealed cavity through the cold air cavity.
10. The turbine hub sealing experimental device according to the previous claim, wherein the cylindrical sealing cold air chamber is coaxially and fixedly arranged in the second cylindrical containing main body section through a support.
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| CN112577755B (en) | 2022-04-19 |
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