CN113062776B - Interstage flow guide disc structure of two-stage gas turbine - Google Patents
Interstage flow guide disc structure of two-stage gas turbine Download PDFInfo
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- CN113062776B CN113062776B CN202110446455.6A CN202110446455A CN113062776B CN 113062776 B CN113062776 B CN 113062776B CN 202110446455 A CN202110446455 A CN 202110446455A CN 113062776 B CN113062776 B CN 113062776B
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- 238000001816 cooling Methods 0.000 claims abstract description 45
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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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
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an interstage guide disc structure of a two-stage gas turbine, which comprises a guide disc, wherein the guide disc comprises: the mounting part is arranged at the connecting end of the first-stage turbine disc and/or the mounting part is arranged at the connecting end of the second-stage turbine disc, and the mounting part is used for connecting the diversion disc with the first-stage turbine disc and the second-stage turbine disc respectively; the abutting part is arranged on the outer wall opposite to the first-stage turbine disk and/or the outer wall opposite to the second-stage turbine disk, and the abutting part is used for sealing between the first-stage turbine disk and the second-stage turbine disk and preventing cooling gas in the cooling channel from leaking; sealing, sealing set up in the outer fringe tip of guiding disk, sealing are used for preventing that the gas from flowing backward and cause one-level turbine dish and the high temperature damage of second grade turbine dish in getting into one-level turbine dish and second grade turbine dish, have the centrifugal load that reduces the guiding disk and all transmit the turbine dish on, are undertaken by the disk body, have improved the life of turbine dish and the effect of reliability.
Description
Technical Field
The present invention relates to the field of turbine engine technology, and in particular, to an interstage diaphragm structure of a two-stage gas turbine.
Background
The gas turbine engine and the ground gas turbine need to seal the stator stages in the operation process of the two-stage gas turbine/high-pressure turbine, high-temperature gas is prevented from flowing backwards, the temperature of a turbine disc is too high, and meanwhile the turbine disc needs to be cooled through external air entraining.
In the inter-stage diversion disc structure of the gas turbine designed in the prior art, a plurality of through holes are processed on the circumferential direction of a diversion disc body passing through an extension section of the disc body, and are installed and fixed by adopting a bolt connection structure; or a plurality of through holes are processed on the extension section of the disc body of the turbine disc and the circumferential direction of the flow guide disc and are installed and fixed by adopting a bolt connection structure; or the locking plate is installed and fixed in a mode of pressing the nut and stopping the locking plate.
No matter the turbine disc is connected through the bolts or fixed through the compression nuts, the centrifugal load of the flow guide disc is transmitted to the turbine disc and borne by the disc body, and the service life and the reliability of the turbine disc are reduced.
Disclosure of Invention
The invention provides an interstage flow guide disc structure of a two-stage gas turbine, which aims to solve the technical problems that the centrifugal load of a flow guide disc is transmitted to a turbine disc and borne by a disc body no matter the flow guide disc is connected by bolts or fixed by compression nuts, and the service life and the reliability of the turbine disc are reduced.
According to one aspect of the invention, an interstage deflector structure of a two-stage gas turbine is provided, which comprises a first-stage turbine disc and a second-stage turbine disc, wherein the first-stage turbine disc and the second-stage turbine disc are connected through end teeth, a deflector disc is arranged between the first-stage turbine disc and the second-stage turbine disc and is tightly abutted against between the first-stage turbine disc and the second-stage turbine disc, flanges are arranged at the centers of the first-stage turbine disc and the second-stage turbine disc, through holes are arranged on the deflector disc and are clamped on the flanges,
the flow guide disc is used for forming a cooling channel together with the first-stage turbine disc and the second-stage turbine disc, and ensuring the sealing of the cooling channel in the working process so as to guide cooling gas to the mortise joint part of the first-stage turbine disc, the mortise joint part of the second-stage turbine disc and blades correspondingly assembled at the mortise joint part and prevent the turbine blades from sliding along the mortise,
the guiding disc includes:
the mounting part is arranged at the connecting end of the first-stage turbine disc and/or the second-stage turbine disc, and the mounting part is used for connecting the diversion disc with the first-stage turbine disc and the second-stage turbine disc respectively;
the abutting part is arranged on the outer wall opposite to the first-stage turbine disk and/or the outer wall opposite to the second-stage turbine disk, and the abutting part is used for sealing between the first-stage turbine disk and the second-stage turbine disk and preventing cooling gas in a cooling channel from leaking;
the sealing part is arranged at the end part of the outer edge of the flow guide disc and used for preventing gas from flowing backwards into the first-stage turbine disc and the second-stage turbine disc to cause the damage of the first-stage turbine disc and the second-stage turbine disc due to overhigh temperature.
By adopting the technical scheme, the turbine engine burns gas when in operation, high-temperature gas enters the turbine disc, the turbine disc is easily damaged, the turbine disc is protected by arranging the diversion disc on the turbine disc, the turbine disc is a first-stage turbine disc and a second-stage turbine disc, the diversion disc is sleeved between the first-stage turbine disc and the second-stage turbine disc and forms a cooling channel with the first-stage turbine disc and the second-stage turbine disc, the diversion disc and the turbine disc are connected in an interference fit and clamped mode through the abutting part on the diversion disc, stress concentration caused by the fact that the turbine disc is installed on the diversion disc in a drilling thread mode is reduced, the service life of the turbine disc and the service life of the diversion disc are reduced, the diversion disc and the turbine disc jointly form a cooling gas channel through the diversion disc, sealing of the channel in the working process is guaranteed, cooling gas is guided to the joggled parts and the blades, turbine blades are prevented from sliding along the mortises, the diversion disc and the turbine disc are abutted and sealed with the turbine disc under the action of the abutting part, damage caused by the high-temperature gas entering the turbine disc is reduced, centrifugal load of the diversion disc is all transmitted to the turbine disc, and the turbine disc is borne, and the bearing effect of the turbine disc is improved.
Further, the installation department includes boss and recess, the boss sets up on the inner wall of through-hole on the water conservancy diversion dish, the recess set up respectively in one-level turbine dish with on the outer wall of second grade turbine dish upper flange, the water conservancy diversion dish passes through the boss respectively the joint in one-level turbine dish the recess and second grade turbine dish in and then set up in one-level turbine dish and on the second grade turbine dish, the water conservancy diversion dish with one-level turbine dish and water conservancy diversion dish with warp between the second grade turbine dish the flange with the through-hole interference fit joint.
Through adopting above-mentioned technical scheme, sealed first-level turbine disk and second grade turbine disk prevent that high temperature gas from getting into the damage that causes the turbine disk in first-level turbine disk and the second grade turbine disk, and through the guiding disk and form cooling channel between turbine disk and the second grade turbine disk and make cooling gas carry out cooling treatment to the turbine disk in getting into first-level turbine disk and second grade turbine disk, and the boss of guiding disk and the recess of turbine disk play prevents changeing the effect, prevents guiding disk circumferential direction.
Furthermore, the flow guiding disc is arranged in a concave manner.
Through adopting the above technical scheme, be the indent setting with the dish body of guiding disk, when turbine dish upper temperature is too big, the guiding disk is out of shape because of the heat production, make the less use that can not influence turbine engine of deformation of guiding disk, through being the indent setting with the dish body of guiding disk, make the cooling channel between guiding disk and the turbine dish narrow, avoid the cooling gas turbulent flow in the cooling channel, and be the indent setting with the dish body of guiding disk and can increase the area of contact of cooling gas and guiding disk, make the cooling effect of guiding disk better.
Further, the abutting portion comprises a abutting plate, the abutting plate is arranged on the side wall of the flow guiding disc, the abutting plate abuts against the first-stage turbine disc and/or the abutting plate abuts against the second-stage turbine disc, and the abutting plate is used for sealing the cooling channel to prevent cooling gas leakage from causing reduction of cooling effects of the first-stage turbine disc and the second-stage turbine disc.
Through adopting above-mentioned technical scheme, butt portion is including supporting the board, the diversion disk is through the outer wall butt of supporting board and turbine disk, through the area of contact of supporting board increase diversion disk and turbine disk, thereby improve the sealing nature of being connected between diversion disk and the turbine disk, avoid high temperature gas to cause the damage to turbine disk and diversion disk in getting into cooling channel, and avoid cooling gas in the cooling channel to reveal through supporting between board and one-level turbine disk and/or supporting board and the second grade turbine disk and cause the cooling effect between diversion disk and one-level turbine disk and the second grade turbine disk to reduce.
Furthermore, one end, far away from the flow guiding disc, of the abutting plate is arranged in a straight manner, and the abutting plate is connected with the first-stage turbine disc and/or the second-stage turbine disc through the straight end.
Through adopting above-mentioned technical scheme, the one end that pastes the board and paste turbine disk sets up to straight end, through straight end through the guiding disk respectively the butt on one-level turbine disk and second grade turbine disk, under the butt of straight end with guiding disk and one-level turbine disk and second grade turbine disk on, the leakproofness of being connected between guiding disk and the turbine disk has been increased, avoided cooling gas to reveal and caused the not good condition that makes turbine disk and guiding disk high temperature damage of cooling effect between guiding disk and the turbine disk to take place, and the board can reduce the guiding disk through straight end and turbine disk butt and be the scratch to the turbine disk in the installation.
Furthermore, the supporting plate is further provided with a containing groove, sealing wires are arranged in the containing groove, and the supporting plate is respectively abutted against the first-stage turbine disc and the second-stage turbine disc and tightly presses the sealing wires in the containing groove against the first-stage turbine disc and the second-stage turbine disc.
Through adopting above-mentioned technical scheme, be provided with the holding tank in supporting the board, will seal the silk butt and establish on the outer wall of guiding disk in the holding tank, at turbine engine during operation, seal the silk tightly and support tightly in the junction of turbine dish and guiding disk and support tightly in the holding tank under the effect of centrifugal force, seal the junction of turbine dish and guiding disk for high temperature gas causes the damage of turbine dish in being difficult to getting into the turbine dish.
Further, sealing part includes the comb tooth end, the comb tooth end sets up on the flow guide plate and is formed with the slow chute on the flow guide plate, the slow chute is used for carrying out buffer storage to the gas impact of gas, stores the gas in reduce in the slow chute that the gas temperature is too high get into the flow guide plate with one-level turbine disk one-level cause the high temperature damage in the second grade turbine disk.
Through adopting above-mentioned technical scheme, the one end that turbine dish was kept away from to the outer fringe of guiding disk is provided with the comb tooth end, is formed with the steadying flow groove between comb tooth end and the guiding disk, carries out the during operation at turbine engine, cushions the impulsive force of gas through the steadying flow groove of comb tooth end department, stabilizes the gas and avoids causing turbine dish and guiding disk high temperature to damage in the gas gets into the turbine dish in the steadying flow groove.
Furthermore, two diversion disks are arranged and are respectively arranged on the first-stage turbine disk and the second-stage turbine disk, gaps are formed at the joints between the diversion disks and the corresponding first-stage turbine disk and/or between the diversion disks and the corresponding second-stage turbine disk, when the engine works, the two diversion disks are tightly abutted in a sealing manner and communicate the diversion disks and the corresponding first-stage turbine disk and the diversion disks and the corresponding cooling channels between the diversion disks and the corresponding second-stage turbine disk for cooling gas transmission, and the tight sealing of the two diversion disks reduces the phenomenon that the gas enters the diversion disks and the first-stage turbine disk and/or the cooling channels between the diversion disks and the second-stage turbine disk to cause the damage of overhigh temperature of the diversion disks, the first-stage turbine disk and the second-stage turbine disk.
By adopting the technical scheme, the flow guide disc is provided with two, be connected one-level flow guide disc and one-level turbine dish, second grade flow guide disc is connected with second grade turbine dish, install in an organic whole through two liang of interference fit with turbine dish and flow guide disc, through the installation that the one-level turbine dish that will install is connected the completion turbine dish with the meshing of second grade turbine dish tip, the effect that makes things convenient for turbine dish and flow guide disc installation has, two flow guide discs respectively with one-level turbine dish and second grade turbine dish between install through little sufficient cooperation, the flow guide disc is in the axial compression state this moment, the thermal expansion of during operation flow guide disc, little sufficient cooperation department becomes clearance fit, flow guide disc rebound that is in the compression state makes the terminal surface laminating of flow guide disc, the centrifugal force of the flow guide disc of high-speed rotation this moment will not load on turbine dish, the life of turbine dish has been improved.
Further, the boss is arranged in a step shape.
Through adopting above-mentioned technical scheme, be the step setting with the boss, when promoting diversion disc and turbine dish interference fit joint, the step form is designed into with installation binding face to the boss terminal surface, and when turbine dish below terminal surface installation was laminated, the clearance was guaranteed with turbine dish recess terminal surface to the boss, prevented to suppress the in-process and led to the fact the damage to diversion disc boss.
Furthermore, a vent groove is arranged between the guide disc and the corresponding first-stage turbine disc and/or between the guide disc and the corresponding second-stage turbine disc, and the vent groove is used for conveying and circulating cooling gas.
Through adopting above-mentioned technical scheme, set up the air channel between turbine dish and guiding disk, with cooling gas through the turbine dish transmit to the guiding disk in and carry out cooling to the turbine dish in the cooling channel, reduce turbine engine work and lead to turbine dish temperature to be in high temperature state always, reduced the life of turbine dish.
The invention has the following beneficial effects:
when the two-stage gas turbine engine works, a flow guide disc is arranged between a first-stage turbine disc and a second-stage turbine disc and comprises a first-stage flow guide disc and a second-stage flow guide disc, the first-stage flow guide disc and the second-stage flow guide disc are respectively connected with the first-stage turbine disc and a flange on the second-stage turbine disc in an interference fit mode through holes, a gap exists between opposite surfaces of the first-stage flow guide disc and the second-stage flow guide disc, the first-stage flow guide disc and the second-stage flow guide disc are abutted against the outer walls of the first-stage turbine disc and the second-stage turbine disc through abutting plates, and sealing wires are abutted against accommodating grooves of the abutting plates during working of the two-stage gas turbine engine to centrifugally abut against the outer walls of the first-stage turbine disc and the second-stage turbine disc to achieve a sealing effect, high-temperature gas can be prevented from entering a cooling channel to cause damage to the turbine discs, and when the two-stage gas turbine engine works, the first-stage flow guide disc and the second-stage flow guide disc move in grooves and form a gap between the first-stage flow guide disc and the second-stage flow guide disc and the cooling channel, and the cooling channel is more stable.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
FIG. 1 is a schematic overall structure of a preferred embodiment of the present invention;
FIG. 2 is a schematic structural view of the preferred embodiment of the present invention taken along the axial line of the first and second stage turbine disks;
fig. 3 is a schematic diagram of an exploded structure of a connection mechanism of a first-stage turbine disc and a first-stage deflector disc in the preferred embodiment of the invention;
fig. 4 is a state diagram of the first-stage diaphragm abutting against the second-stage diaphragm in accordance with the preferred embodiment of the present invention;
fig. 5 is an axial sectional view of the diaphragm of fig. 1.
Illustration of the drawings:
1. a first stage turbine disk; 2. a secondary turbine disk; 3. a first-stage flow guide disc; 4. a second stage flow guide disc; 5. an installation part; 51. a boss; 52. a groove; 6. an abutting portion; 61. a resisting plate; 62. accommodating grooves; 63. sealing the filaments; 7. a sealing part; 71. a grate tooth end; 72. a flow stabilizing groove; 8. a cooling channel; 9. a vent groove.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the drawings, but the invention can be practiced in many different ways, which are defined and covered by the following.
Referring to fig. 1 and 2, the embodiment discloses an interstage diaphragm structure of a two-stage gas turbine, including a turbine disk, the turbine disk includes a first-stage turbine disk 1 and a second-stage turbine disk 2, a diaphragm is provided between the first-stage turbine disk 1 and the second-stage turbine disk 2, the diaphragm includes a first-stage diaphragm 3 and a second-stage diaphragm 4, the first-stage diaphragm 3 and the second-stage diaphragm 4 both include an installation part 5, an abutting part 6 and a sealing part 7, the first-stage turbine disk 1 is engaged with the second-stage turbine disk 2, the first-stage diaphragm 3 is abutted with the second-stage diaphragm 4 between the first-stage turbine disk 1 and the second-stage turbine disk 2, the installation part 5 includes a boss 51 and a groove 52, the groove 52 is respectively opened on the first-stage turbine disk 1 and the second-stage turbine disk 2 and is located on the outer wall of the protruding end of the turbine disk close to the diaphragm, the boss 51 is respectively welded on the inner wall of the boss 51 of the first-stage diaphragm 3 and the second-stage diaphragm 4, the shape of the boss 51 is in a step-like arrangement to reduce the propulsion damage of the boss 51, the boss 51 and the boss 51 is clamped with the boss 52 in an interference fit with the boss 4, and the boss 51 is connected with the second-stage turbine disk, and the boss 4, and the boss is connected with the boss on the second-stage turbine disk at the opposite surface of the first-stage turbine disk 1. When the engine works, the upper part of the diversion disc is in contact with gas, and the temperature of the diversion disc is higher than that of the turbine disc due to heat conduction, meanwhile, the thermal expansion change amount is larger than that of the turbine disc due to the thin-wall structure, the interference fit surface between the diversion disc and the turbine disc becomes a small gap, the diversion disc in a compression state rebounds, the opposite surfaces of the first-level diversion disc 3 and the second-level diversion disc 4 are pressed and attached relatively, and then the cooling channel 8 communicated with the diversion disc is formed for cooling gas to enter and cool the engine.
Referring to fig. 2 and 3, the diversion disc is arranged between the first-stage turbine disc 1 and the second-stage turbine disc 2, one side of the disc body of the diversion disc, which is close to the turbine disc, is in an inward concave arrangement, and a cooling channel 8 is formed between the inward concave disc body of the diversion disc and the turbine disc, so that the transmission flow of cooling gas of the cooling channel 8 can be reduced. The turbulence of cooling gas in the cooling channel 8 is reduced, and the disc body of the flow guide disc is arranged to be concave and can be installed in cooperation with the turbine disc.
Referring to fig. 2 and 3, abutting portion 6 includes abutting plate 61, abutting plate 61 is disposed on the outer ring of the flow guide disc, abutting plate 61 abuts against the cooling channel 8 on the turbine disc, and the turbine disc and the flow guide disc are connected through abutting plate 61, high-temperature damage of the turbine disc caused by gas entering the flow guide disc and the turbine disc and high-temperature damage of the turbine disc and the flow guide disc caused by cooling gas leakage in the cooling channel are reduced, one end, close to the turbine disc, of abutting plate 61 is set to be a straight end, the contact surface between the turbine disc and the flow guide disc is increased on the turbine disc through abutting of the straight end of abutting plate 61, and connection sealing performance between the turbine disc and the flow guide disc is improved. Support and be provided with holding tank 62 on the board 61, be provided with the silk 63 of obturating in holding tank 62, the silk 63 of obturating is located holding tank 62 and the butt on the outer wall of turbine dish, and when the turbine dish was rotatory, the centrifugation of the silk 63 of obturating was supported tightly and is avoided gas infiltration to lead to turbine dish high temperature to damage and cooling gas to reveal and cause the unable damage of cooling down in time of turbine dish between the junction of supporting board 61 and turbine dish with turbine dish and flow guide disc.
Referring to fig. 2, 4 and 5, the sealing portion 7 includes a comb tooth end 71, the comb tooth end 71 is fixed on one side of the first-stage flow guiding plate 3 and the second-stage flow guiding plate 4 away from the turbine disc, and a flow stabilizing groove 72 is formed between the comb tooth end 71 and the first-stage flow guiding plate 3 and the second-stage flow guiding plate 4, so that the impact of the gas is buffered through the flow stabilizing groove at the comb tooth end, and the gas is stabilized in the flow stabilizing groove, thereby preventing the gas from entering the turbine disc and causing high-temperature damage to the turbine disc and the flow guiding plate. Set up the air channel 9 of intercommunication on the boss 51 inner wall of guiding disk and the boss 51 outer wall of turbine dish, supply cooling gas to penetrate through air channel 9 and carry out the cooling of turbine dish and handle, improved the life of turbine dish.
The working principle of the interstage diaphragm structure of the two-stage gas turbine is as follows: when the two-stage gas turbine engine works, a flow guide disc is arranged between a first-stage turbine disc 1 and a second-stage turbine disc 2 and comprises a first-stage flow guide disc 3 and a second-stage flow guide disc 4, the first-stage flow guide disc 3 and the second-stage flow guide disc 4 are respectively connected with flanges on the first-stage turbine disc 1 and the second-stage turbine disc 2 through holes in an interference fit manner, gaps exist between opposite surfaces of the first-stage flow guide disc 3 and the second-stage flow guide disc 4, the first-stage flow guide disc 3 and the second-stage flow guide disc 4 are abutted to outer walls of the first-stage turbine disc 1 and the second-stage turbine disc 2 through abutting plates 61, and sealing wires 63 are abutted to inner concave portions of accommodating grooves 62 of the abutting plates 61 during working of the two-stage gas turbine engine through sealing wires 63 to perform a sealing effect on the outer walls of the first-stage turbine disc 1 and the second-stage turbine disc 2 during working, so that the opposite surfaces of the first-stage flow guide disc 3 and the second-stage flow guide disc 4 are tightly abutted to prevent high-temperature gas from entering cooling channels 8, and when the two-stage gas turbine engine works, the first-stage gas turbine disc 3 and the two-stage flow guide disc 4 are communicated with the gaps between the first-stage flow guide disc 3 and the second-stage flow guide disc 2, and the cooling channels, and the gap between the second-stage flow guide disc 2, and the first-stage flow guide disc 2, and the gap between the first-stage flow guide disc 2 is formed between the gap formed between the second-stage flow guide disc 2, and the cooling channels, and the gap formed between the first-stage flow guide disc 2, and the second-stage flow guide disc 2, and the gap formed between the cooling channel formed between the second flow guide disc 2, and the cooling channel.
Example 2
The present embodiment is different from embodiment 1 in that: butt portion 6 is including supporting board 61, supports board 61 and sets up on the outer wall that the guiding plate is close to the perisporium on the guiding plate, processing have on the outer wall of turbine dish with support the butt groove of board 61 laminating, with the connecting area of contact between guiding plate and the turbine dish of the supporting board 61 butt increase guiding plate of guiding plate in the butt groove for the sealing nature of being connected between guiding plate and the turbine dish improves, avoids causing the damage of turbine dish in the high temperature gas gets into cooling channel 8.
Example 3
This embodiment and embodiment 1's difference lie in that installation department 5 is provided with the whorl including setting up on the 1 protruding end's of the whorl one-level turbine disk outer wall on the protruding end inner wall of guiding disk, it is fixed in turbine disk threaded connection through the guiding disk, the spacing groove has been seted up in the threaded connection department of guiding disk and turbine disk, it has spacing key to peg graft in the spacing groove, turn to the location to turbine disk and guiding disk and retrograde motion through spacing key, avoid taking place between guiding disk and the turbine disk to reverse, cause turbine engine unable work.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. An interstage diaphragm structure of a double-stage gas turbine, which comprises a first-stage turbine disk (1) and a second-stage turbine disk (2), wherein the first-stage turbine disk (1) and the second-stage turbine disk (2) are connected through end teeth, and the interstage diaphragm structure is characterized in that: a flow guide disc is arranged between the first-stage turbine disc (1) and the second-stage turbine disc (2), the flow guide disc is tightly propped against between the first-stage turbine disc (1) and the second-stage turbine disc (2), flanges are arranged at the centers of the first-stage turbine disc and the second-stage turbine disc, a through hole is arranged on the flow guide disc, the through hole is clamped on the flange,
the flow guide disc is used for forming a cooling passage (8) together with the first-stage turbine disc (1) and the second-stage turbine disc (2) and ensuring the sealing of the cooling passage (8) in the working process so as to guide cooling gas to a mortise part of the first-stage turbine disc (1), a mortise part of the second-stage turbine disc (2) and blades correspondingly assembled at the mortise parts and prevent the turbine blades from sliding along the mortises,
the guiding disc includes:
the mounting part (5), the mounting part (5) be used for the water conservancy diversion dish respectively with the connection of one-level turbine dish (1) and second grade turbine dish (2), mounting part (5) include boss (51) and recess (52), boss (51) set up on the inner wall of water conservancy diversion dish upper bore, recess (52) set up respectively in one-level turbine dish (1) with on the outer wall of second grade turbine dish (2) upper flange, the water conservancy diversion dish pass through boss (51) joint respectively in recess (52) of one-level turbine dish (1) and recess (52) of second grade turbine dish (2) and then set up on one-level turbine dish (1) and second grade turbine dish (2), boss (51) are the step;
the abutting part (6) is arranged on the outer wall opposite to the first-stage turbine disk (1) and the abutting part (6) is arranged on the outer wall opposite to the second-stage turbine disk (2), and the abutting part (6) is used for sealing between the first-stage turbine disk (1) and the second-stage turbine disk (2) and preventing cooling gas in a cooling channel from leaking;
the sealing part (7) is arranged at the end part of the outer edge of the flow guide disc, the sealing part (7) is used for preventing gas from reversely flowing into the first-stage turbine disc and the second-stage turbine disc to cause the damage of the first-stage turbine disc and the second-stage turbine disc due to overhigh temperature,
the flow guide disc is provided with two, one-level flow guide disc (3) is connected with one-level turbine disc (1), second grade flow guide disc (4) is connected with second grade turbine disc (2), install in an organic whole through two liang of interference fit with turbine disc and flow guide disc, through the installation of accomplishing turbine disc with first grade turbine disc (1) and second grade turbine disc (2) end meshing connection that will install, the effect of making things convenient for turbine disc and flow guide disc installation has, two flow guide discs respectively with between one-level turbine disc (1) and second grade turbine disc (2) through little interference fit installation, the flow guide disc is in the axial compression state this moment, there is the clearance in the opposite face of one-level flow guide disc (3) and second grade flow guide disc (4), the during operation flow guide disc thermal expansion, little interference fit department becomes clearance fit, the flow guide disc that is in compression state makes the terminal surface laminating of two flow guide discs bounce.
2. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 1, wherein: the flow guide disc is arranged in an inwards concave manner.
3. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 1, wherein: the abutting part (6) comprises abutting plates (61), the abutting plates (61) are arranged on the side wall of the flow guide disc, the abutting plates (61) abut against the first-stage turbine disc (1) and the second-stage turbine disc (2), and the abutting plates (61) are used for sealing the cooling channel (8) to avoid cooling gas leakage to reduce the cooling effect of the first-stage turbine disc (1) and the second-stage turbine disc (2).
4. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 3, wherein: one end, far away from the flow guide disc, of the abutting plate (61) is arranged in a straight mode, and the abutting plate (61) abuts against the first-stage turbine disc (1) and the second-stage turbine disc (2) through the straight end.
5. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 3, wherein: the supporting plate (61) is further provided with an accommodating groove (62), a sealing wire (63) is arranged in the accommodating groove (62), the supporting plate (61) is abutted to the first-stage turbine disc (1) and the second-stage turbine disc (2) respectively and compresses the sealing wire (63) in the accommodating groove (62) to the first-stage turbine disc (1) and the second-stage turbine disc (2).
6. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 1, wherein: sealing portion (7) are including comb tooth end (71), comb tooth end (71) set up on the flow guide plate and are formed with flow stabilization groove (72) on the flow guide plate, flow stabilization groove (72) are used for carrying out the buffer storage to the gas.
7. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 1, wherein: when the engine works, the two diversion disks are tightly sealed and communicated with a cooling channel (8) between the diversion disk and the corresponding first-stage turbine disk (1) and between the diversion disk and the corresponding second-stage turbine disk (2) for conveying cooling gas, and the tight sealing of the two diversion disks reduces the damage of overhigh temperature of the diversion disk, the first-stage turbine disk (1) and the second-stage turbine disk (2) caused by the fact that gas enters the diversion disk and the cooling channel between the first-stage turbine disk (1) and between the diversion disk and the second-stage turbine disk (2).
8. The interstage diaphragm structure of a dual stage gas turbine as claimed in claim 1, wherein: and vent grooves (9) are arranged between the diversion disc and the corresponding first-stage turbine disc (1) and between the diversion disc and the corresponding second-stage turbine disc (2), and the vent grooves (9) are used for conveying and circulating cooling gas.
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| CN202110446455.6A CN113062776B (en) | 2021-04-25 | 2021-04-25 | Interstage flow guide disc structure of two-stage gas turbine |
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| CN202110446455.6A CN113062776B (en) | 2021-04-25 | 2021-04-25 | Interstage flow guide disc structure of two-stage gas turbine |
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| CN113062776B true CN113062776B (en) | 2022-12-16 |
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| CN113339077B (en) * | 2021-07-08 | 2022-06-28 | 中国航发湖南动力机械研究所 | Flow guide disc mounting connection and sealing structure |
| CN113623020B (en) * | 2021-08-02 | 2022-07-08 | 无锡友鹏航空装备科技有限公司 | Turbine guider that leakproofness is high |
| CN114109511B (en) * | 2021-11-12 | 2024-06-18 | 中国航发沈阳发动机研究所 | Novel disk core connection structure and double-radial-plate turbine disk with same |
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| FR2663997B1 (en) * | 1990-06-27 | 1993-12-24 | Snecma | DEVICE FOR FIXING A REVOLUTION CROWN ON A TURBOMACHINE DISC. |
| CN104895622B (en) * | 2015-06-24 | 2016-08-24 | 中国航空动力机械研究所 | A kind of gas turbine flow guiding disc |
| CN106523037A (en) * | 2016-12-12 | 2017-03-22 | 中国燃气涡轮研究院 | A turbine baffle structure with a high-level pre-swirl flow path |
| CN111441828B (en) * | 2020-03-12 | 2022-09-16 | 中国科学院工程热物理研究所 | An engine turbine disk cavity structure with a pre-swirl nozzle and a guide plate |
| CN112282853B (en) * | 2020-10-29 | 2022-06-03 | 中国航发湖南动力机械研究所 | Two-stage turbine and engine |
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