CN112324570A - Turbine disk driving device and gas turbine using same - Google Patents
Turbine disk driving device and gas turbine using same Download PDFInfo
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- CN112324570A CN112324570A CN202011233644.7A CN202011233644A CN112324570A CN 112324570 A CN112324570 A CN 112324570A CN 202011233644 A CN202011233644 A CN 202011233644A CN 112324570 A CN112324570 A CN 112324570A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
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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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a turbine disk driving device and a gas turbine using the same, wherein the gas turbine comprises a turbine disk mechanism, a transmission shaft mechanism, a casing system and a supporting system, wherein the turbine disk mechanism is fixedly arranged on the transmission shaft mechanism; the transmission shaft mechanism is arranged in the casing system through a bearing; the casing system is fixed on a bracket of the supporting system; the turbine disc mechanism comprises more than one turbine disc, each turbine disc comprises a stator assembly and a rotor assembly, and the stator assembly comprises a stator shell and a stator vane arranged in an inner cavity of the stator shell around a circle. The invention takes high-pressure gas as a working medium, and carries out centralized redistribution after entering an energy conversion link, and utilizes the structure of a turbine disc to redirect the working medium to an area with the largest working radius for torsion generation and output mechanical power; the multi-stage energy conversion is synchronously completed by adopting multi-point graded attenuation, the vector energy efficiency under different rates is guaranteed, and the energy-saving and emission-reducing system is dedicated to energy conservation and emission reduction.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a turbine disk driving device and a gas turbine applying the same.
Background
The gas turbine is a heat engine system which is compressed by an air compressor through sucking air, is mixed with a combustion medium, is combusted and expanded by a combustion chamber and is converted into mechanical energy through a turbine, and has the advantages of large power output, small equipment volume, simple structure, easy maintenance and the like; the defects are that the consumption is large, the mobility response is slow, the row amplification is large, the turbine blade is difficult to cool, the manufacturing threshold of the material is high, and the like. Gas turbines are currently heavily weighted in equipment manufacturing and take an irreplaceable position in certain equipment.
Disclosure of Invention
The invention aims to solve the technical problem of a turbine disk driving device and a gas turbine applying the same, and aims to change the current situation of the gas turbine, optimize and perfect the short plate and solve the defects in the prior art.
The invention is realized by the following technical scheme: a turbine disk driving device comprises a turbine disk mechanism, a transmission shaft mechanism, a casing system and a supporting system, wherein the turbine disk mechanism is fixedly arranged on the transmission shaft mechanism; the transmission shaft mechanism is arranged in the casing system through a bearing; the casing system is fixed on a bracket of the supporting system;
the turbine disc mechanism comprises more than one turbine disc, each turbine disc comprises a stator component and a rotor component, and the stator component comprises a stator shell and a stator stationary vane which is arranged in an inner cavity of the stator shell in a surrounding mode;
the rotor assembly comprises a rotor disc and more than one group of composite air passage structures distributed along the outer circular surface of the rotor disc, a working medium inlet is formed in one side of the middle of the rotor disc, a bearing ring is arranged in the middle of the working medium inlet, centrifugal turbine blades are connected around the bearing ring and used for structurally connecting and intensively leading in working media to the centrifugal turbine blades, and a centrifugal diversion air passage is formed in the position, corresponding to each group of composite air passage structures, in the rotor disc;
the output end of the centrifugal flow guide air passage is connected with the air inlet end of the composite air passage structure, the centrifugal turbine blade is used for connecting the rotor disc and the bearing lantern ring and distributing working media to the centrifugal flow guide air passage from the inside of the rotor disc, the windward rotation direction of the centrifugal turbine blade is synchronous with the rotor, and the root part of the centrifugal turbine blade is axially through;
the centrifugal flow guide air passage is used for compressing and conveying working media to the main nozzle, the main nozzle is formed by rotor movable blades, the working media are ejected from the main nozzle in a reverse direction to rotate to obtain reverse kinetic energy, and an expansion air port is arranged on the back side of the main nozzle to buffer and start to release energy to the main nozzle;
each group of composite air passage structures are also provided with an air outlet, after the work is done, the surplus working medium is discharged from the air outlet in the opposite direction of the rotation of the rotor, and the middle of the rotor disc is provided with more than one ventilation hole for heat dissipation.
As a preferred technical scheme, the composite air flue structure all includes an extension gas port, the main nozzle, the first air inlet that sets up side by side with the main nozzle, the first jet orifice that switches on through the composite air flue with the first air inlet, the second air inlet that sets up side by side with the first jet orifice, the second jet orifice that switches on through the composite air flue with the second air inlet, the third air inlet that sets up side by side with the second jet orifice, the third jet orifice that switches on through the composite air flue with the third air inlet, the fourth air inlet that sets up side by side with the third jet orifice, the fourth jet orifice that switches on through the composite air flue with the fourth air inlet, the fifth air inlet that sets up side by side with the fourth jet orifice, the fifth air inlet output communicates with each other with the gas vent.
As a preferred technical scheme, the radial inclination angle of the rotor movable vane is consistent with that of the stator vane, and the gap between the rotor movable vane and the stator vane is a space for working medium to do work through expansion.
Preferably, a non-contact type air seal ring is arranged at the joint of the rotor disc and the stator shell.
As a preferred technical scheme, the transmission shaft mechanism comprises a rotor air inlet and outlet connecting ring, a sealing telescopic ring, a rotor air inlet sealing cover, a power output end, a high-pressure rotor air sealing ring, a double-layer bearing ring, a reducing adjusting control valve, a centrifugal reducing self-adaptive adjusting valve and a turbine connecting bearing, wherein the turbine disc comprises a low-speed turbine disc and a high-speed turbine disc, the double-layer bearing ring is used for connecting a casing connecting port and installing a double-layer sleeve shaft structure of a main transmission shaft and the high-speed turbine transmission shaft, the rotor air inlet and outlet connecting ring is used for connecting a combustion chamber and the turbine disc, the sealing telescopic ring is made of a ductile metal material, the high-speed turbine transmission shaft is connected with a compressor driving wheel and used for driving the compressor to operate, the turbine connecting bearing is connected with the reducing adjusting control valve between the high-speed turbine and the low-, the air inlet and outlet connecting ring is used for connecting a rotor air port sealing cover, and the rotor air port sealing cover is used for sealing an air passage at the tail end of the turbine disk module.
As a preferred technical scheme, the reducing adjusting control valve comprises a control valve outer frame, a control valve inner support, a control valve pull rod, a control valve sheet and a control valve rotating shaft; the two control valve inner supports are arranged in the middle of the control valve outer frame and are arranged in an inner and outer ring structure, the two control valve inner support supports are connected through more than one control valve pull rod, two ends of each control valve pull rod are respectively connected with the two control valve inner supports through control valve rotating shafts, and a control valve door sheet is arranged in the middle of each control valve inner support of the inner ring;
the centrifugal diameter-changing self-adaptive regulating valve comprises a regulating valve outer frame, a regulating valve inner support, a regulating valve elastic pressing sheet, a regulating valve sheet and a regulating valve rotating shaft, wherein the regulating valve inner support is arranged in the middle position of the regulating valve outer frame, the regulating valve sheet is connected with the regulating valve inner support through the regulating valve rotating shaft, the regulating valve elastic pressing sheet presses the regulating valve sheet towards the circle center, one end of the regulating valve sheet is elastically connected with the inner side face of the regulating valve outer frame, and the other end of the regulating valve.
The casing system comprises a casing, an outer duct, a casing framework, a main transmission shaft bearing, a high-pressure vortex disc, a compressor bearing, an exhaust hole and a high-pressure turbine bearing, wherein the casing is divided into an upper part and a lower part, a stator casing and stator blades are arranged in the casing, the main transmission shaft bearing is connected with the casing through the casing framework, the outer duct is formed among the casing frameworks, the output end of the exhaust hole of the turbine disc is communicated with the exhaust hole, the exhaust hole is communicated with the outer duct, the length of the exhaust hole is equal to the distance between the two turbine discs, the width of the exhaust hole is 0.5 of 36 minutes of the circumference of a circle, namely, each hole is 5 degrees, the hole width and the interval are equal, after being discharged from the exhaust hole of the turbine disc, the residual gas drives the residual working medium to be discharged outwards through the exhaust hole on the inner wall of the.
As a preferred technical scheme, the support system comprises a base and a bracket, wherein the base is arranged at the bottom of the bracket, and the bracket is used for installing a shell of the support system.
The composite air passage comprises two parts, namely two side air passages and a middle air passage, the working medium is sprayed out from a main nozzle of the middle air passage of the rotor and enters through the stator blades to counter pressure the air passages on the two sides of the rotor, and the sum of the sectional areas of the two side air passages is larger than or equal to the sectional area of the middle air passage.
A gas turbine includes a gas turbine mounted with a turbine disk drive.
The invention has the beneficial effects that: the invention adopts a working medium centralized redistribution mode, and utilizes a turbine disk structure to redirect the working medium to an area with the largest working radius for torque generation; and the method adopts graded acting to refine energy absorption and conversion to replace a turbine layer-by-layer axial inclination blowing pressure acting mode, thereby improving the conversion efficiency and the maneuvering response capability of the gas turbine.
Compared with the prior art, the invention changes the axial array layout of the stator and the rotor of the turbine disk into the radial alignment and fit layout, redefines the working area and the working mode to maximize the torque output, reduces the strict working condition range, and more importantly, the relatively independent structure of the turbine disk greatly increases the interface convenient for cooling operation to reduce the use amount of high-value materials, thereby reducing the cost
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without any creative effort.
FIG. 1 is a schematic cross-sectional view of a complete layout of a turbine disk drive;
FIG. 2 is an exploded isometric view of the turbine disk drive;
FIG. 3 is an exploded view of the stator and rotor of the turbine disk;
FIG. 4-1 is a side elevational view of a turbine disk;
FIG. 4-2 is a side sectional view of a turbine disk;
4-3 are side sectional pictorial views of a turbine disk;
FIG. 5 is a somewhat diagrammatic perspective pictorial view of a turbine disk;
FIG. 6 is a top plan view of a turbine disk;
FIG. 7 is a cross-sectional view of the turbine disk bulk, two-sided gas path;
FIG. 8 is a cross-sectional view of a turbine disk bulk core gas path;
FIG. 9 is a front pictorial view of a derivative prototype of a turbine disk;
FIG. 10 is a rear perspective view of a derivative version of a turbine disk;
FIG. 11-1 is a front view of a variable diameter modulating control valve;
FIG. 11-2 is a reverse side view of the variable diameter modulating control valve;
FIG. 12-1 is a perspective pictorial view of a variable diameter modulating control valve;
FIG. 12-2 is a perspective pictorial view of another angle of view of the variable diameter modulating control valve;
FIG. 13-1 is an elevation view of a centrifugal adaptive variable diameter valve;
FIG. 13-2 is an elevation view of another perspective of the centrifugal adaptive variable diameter valve;
FIG. 14-1 is a perspective pictorial view of a centrifugal adaptive variable diameter valve;
FIG. 14-2 is a perspective illustrative view of another perspective of the adaptive variable diameter centrifugal valve.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations where mutually exclusive features and/or steps are present.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
In the description of the present invention, it is to be understood that the terms "one end", "the other end", "outside", "upper", "inside", "horizontal", "coaxial", "central", "end", "length", "outer end", and the like, indicate orientations or positional relationships based on those shown in the drawings, merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Further, in the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
The use of terms such as "upper," "above," "lower," "below," and the like in describing relative spatial positions herein is for the purpose of facilitating description to describe one element or feature's relationship to another element or feature as illustrated in the figures. The spatially relative positional terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary term "below" can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly
In the present invention, unless otherwise explicitly specified or limited, the terms "disposed," "sleeved," "connected," "penetrating," "plugged," and the like are to be construed broadly, e.g., as a fixed connection, a detachable connection, or an integral part; can be mechanically or electrically connected; either directly or indirectly through intervening media, or may be interconnected between two elements or in a relationship wherein two elements interact, unless expressly specified otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
More specific details of the invention will be described in relation to the use of a turbine disk drive for a gas turbine engine, it being understood that the turbine disk drive as described hereinafter may also be used in other systems such as, but not limited to, steam engines, compressed air locomotives, pneumatic engineering tools and the like.
As shown in fig. 1 and fig. 2, a turbine disk driving device of the present invention includes a turbine disk mechanism 1, a transmission shaft mechanism 2, a casing system 3 and a support system 4, wherein the turbine disk mechanism 1 is fixedly mounted on the transmission shaft mechanism 2; the transmission shaft mechanism 2 is arranged in the casing system 3 through a bearing; the casing system 3 is fixed on a bracket of the support system 4;
the turbine disc mechanism comprises more than one turbine disc, each turbine disc comprises a stator assembly and a rotor assembly, and the stator assembly comprises a stator shell 101 and a circle of stator vanes 102 arranged in the inner cavity of the stator shell 101 in a surrounding mode;
the rotor assembly comprises a rotor disc 100, a rotor cavity 103 is arranged in the rotor disc 100, more than one group of composite air passage structures are distributed along the outer circular surface of the rotor disc 100, a working medium inlet is arranged at one side of the circular middle of the rotor disc 100, which is used for inputting working medium, a bearing ring 113 is arranged at the center of the working medium inlet, centrifugal turbine blades 105 are arranged outside the bearing ring 113 and used for structurally connecting and intensively leading the working medium into the centrifugal turbine blades, and a centrifugal guide air passage 106 is arranged at the position, corresponding to each group of composite air passage structures, of the rotor disc 100;
the output end of the centrifugal guide air passage 106 is connected with the air inlet ends which are arranged in parallel in the composite air passage structure through the stator blade clearance, the centrifugal turbine blade 105 is used for structural connection of the rotor disc 100 and the bearing lantern ring and distributing working media into the rotor disc 100 to the centrifugal guide air passage 106, the windward rotation direction of the centrifugal turbine blade 105 is synchronous with the rotor, and the root part is axially through;
the centrifugal guide air passage 106 is used for compressing and conveying working media to the main nozzle 108, the main nozzle 108 is formed by rotor movable blades, the working media are ejected from the main nozzle 108 in the opposite direction to obtain opposite kinetic energy, and an expansion air port 1111 is further arranged on a rotating shaft disc located on one side of the back face of the main nozzle 108 and used for buffering and starting to release energy to the main nozzle;
each group of composite air passage structures is also provided with an air outlet 110, after the work is done, the surplus working medium is discharged from the air outlet 110 to the opposite direction of the rotation of the rotor, and the middle of the rotor disc 100 is provided with more than one air hole 109 for ventilation and heat dissipation.
In this embodiment, the composite air channel structure includes an expansion air port 1111, the main air port 108, a first air inlet 1112 arranged side by side with the main air port 108, a first air outlet 1113 communicated with the first air inlet 1112 through the composite air channel 111, a second air inlet 1114 arranged side by side with the first air outlet 1113, a second air outlet 1115 communicated with the second air inlet 1114 through the composite air channel 111, a third air inlet 1116 arranged side by side with the second air outlet 1115, a third air outlet 1117 communicated with the third air inlet 1116 through the composite air channel, a fourth air inlet 1118 arranged side by side with the third air outlet 1117, a fourth air outlet 1119 communicated with the fourth air inlet 1118 through the composite air channel, a fifth air inlet 1120 arranged side by side with the fourth air outlet 1119, and an output end of the fifth air inlet 1120 is communicated with the exhaust port.
The radial inclination angle of the rotor moving blade 107 is the same as that of the stator blade 102, the gap between the rotor moving blade and the stator blade is a space for the working medium to do work by expansion, and the fitting part of the rotor disk 100 and the stator casing 101 is provided with a non-contact type air seal ring 103.
In the embodiment, the transmission shaft mechanism comprises a rotor air inlet and outlet connecting ring 201, a sealing telescopic ring 202, a rotor air inlet cover 203, a power output end 204, a high-pressure rotor air sealing ring 205, a double-layer bearing ring 206, a reducing regulation control valve 207, a centrifugal reducing self-adaptive regulation valve 208 and a turbine connecting bearing 209, wherein the turbine disk comprises a low-speed turbine disk and a high-speed turbine disk, the double-layer bearing ring 206 is used for connecting a casing connecting port and installing a main transmission shaft and a high-speed turbine transmission shaft, the rotor air inlet and outlet connecting ring 201 is used for connecting a combustion chamber and the turbine disk, the sealing telescopic ring 202 is made of a ductile metal material, the high-speed turbine transmission shaft is connected with a compressor driven wheel and used for driving the compressor to run, the turbine connecting bearing 209 is connected with the reducing regulation control valve 207 between the high-speed turbine and the low-speed turbine, and the centrifugal self-adaptive reducing, inlet and outlet connection rings 201 are used for connection between the rotors 100, and a gas port cover 203, the rotor gas port cover 203 being used for gas path sealing at the end of the turbine disk module.
The variable-diameter adjusting control valve comprises a control valve outer frame 2071, a control valve inner support 2072, a control valve pull rod 2073, a control valve plate 2074 and a control valve rotating shaft 2075; the two control valve inner supports 2072 are arranged in the middle of the control valve outer frame, the two control valve inner supports are arranged in an inner and outer ring structure, the two control valve inner supports are connected through more than one control valve pull rod, two ends of the control valve pull rod are respectively connected with the two control valve inner supports through control valve rotating shafts, and a control valve disk is arranged in the middle of the control valve inner support of the inner ring;
the centrifugal reducing self-adaptive regulating valve comprises a regulating valve outer frame 2081, a regulating valve inner frame 2082, a regulating valve elastic pressing sheet 2083, a regulating valve sheet 2084 and a regulating valve rotating shaft 2085, wherein the regulating valve inner frame is arranged at the middle position of the regulating valve outer frame, the regulating valve sheet is connected with the regulating valve inner frame through the regulating valve rotating shaft, the regulating valve elastic pressing sheet presses the regulating valve sheet 2084 towards the circle center, one end of the regulating valve elastic pressing sheet is elastically connected with the inner side surface of the regulating valve outer frame, and the other end of the.
The casing system comprises a shell 301, an outer duct 302, casing frameworks 303, a main transmission shaft bearing 304, a high-pressure scroll connecting compressor bearing 305, an exhaust hole 306 and a high-pressure turbine bearing 307, wherein the shell is divided into an upper part and a lower part, a stator shell and stator blades are arranged in the shell, the main transmission shaft bearing 304 is connected with the shell through the casing frameworks 303, the outer duct is formed among the casing frameworks, the output end of a turbine disk exhaust hole 110 is communicated with the exhaust hole 306, the exhaust hole is communicated with the outer duct, the length of the exhaust hole 306 is equal to the distance between two turbine disks, the width of the exhaust hole is 0.5 of 36 minutes of the circumferential length, namely, each hole is 5 degrees, the hole width and the interval are equal, after the residual gas is exhausted from the turbine disk exhaust hole 110, the residual gas drives working medium to be exhausted outwards through the exhaust hole 306 on the inner wall of.
In this embodiment, the support system includes a base 401 and a bracket 402, the base 401 is disposed at the bottom of the bracket 402, and the bracket 402 is used for installing the housing of the support system.
The composite air passage 111 comprises two parts of two side air passages and a middle air passage, the working medium is sprayed out from the main jet orifice 108 of the middle air passage of the rotor and enters through the stator blade to counter pressure the air passage orifices on the two sides of the rotor, and the sum of the sectional areas of the two side air passages is larger than or equal to the sectional area of the middle air passage.
The casing body is divided into two modules, the two modules are divided by the axis of the transmission shaft 2 and transversely divided, and the circular section of the inner wall of the casing body is divided into an upper module and a lower module, so that the installation is convenient; the casing 3 is fastened to the bracket 402 on both sides; the exhaust mode of the turbine disc device 1 is the side exhaust, so that an outer duct 302 is required to be added for exhausting, the residual gas is exhausted from the turbine disc exhaust hole 110 and then drives the residual working medium to be exhausted outwards by centrifugal force, and the residual working medium is exhausted to the outer duct through an exhaust hole 306 on the inner wall of the casing;
the drive shaft portion shown in fig. 2, from the interface of the turbine disk drive and the combustor to the end, is arranged in the following order: the first and double-layer bearings 206 are used for installing a main transmission shaft and a high-speed turbine transmission shaft on a casing connecting port; secondly, the connecting ring 201 is used for connecting and fixing each turbine disk 1 module and the centrifugal adaptive reducing valve 208 on the transmission shaft, wherein the telescopic ring 202 is made of ductile metal so as to adapt to temperature difference with larger temperature; thirdly, the high-speed turbine disc 1 (connected with a driving wheel of the compressor in the front) is used for converting energy to drive the compressor to operate, and the diameter of the high-speed turbine disc 1 is slightly smaller than that of the low-speed turbine disc 1 so as to adapt to the response speed of high-speed operation; fourthly, a bearing 209 is used for connecting a reducing regulating valve 207 between the high-speed turbine and the low-speed turbine; fifthly, the variable diameter regulating valve 207 is used for regulating the artificial variable of the working medium at low speed and high speed; the sixth low-speed turbine disc 1 is used for converting energy to drive a main power output end; then, connecting a plurality of modules of the turbine disk 1 repeatedly, wherein the eighth connecting ring 201 is used for connecting a ninth sealing cover 203 (a tail end sealing ring is not provided with a regulating valve) and a telescopic ring 202; the tenth sealing cover 203 is used for sealing an air passage at the tail end of the turbine disk module and has the function of a safety valve, and the safety valve is used for preventing overload; eleventh, power output 204 (the front or rear layout of the start and output can be flexibly selected according to the requirements of different devices).
Stator of the turbine disk: 3-10, as shown in fig. 3, the stator of the turbine disk is divided into a casing 101 and a blade 102, because the stator is the most severe part, the blade and the casing need to be arranged in a relatively sufficient hollow cooling layout, the material needs to be coated with ceramic on the outside by using cobalt-based or nickel-based metal with higher heat-resisting grade, although the working condition of the stator is severe, the stator is static after all, and in the case of sufficient cooling, the added precious metal component can be reduced by a proper amount; the shell and the blade group of the stator are highly matched with the rotor, the clearance is minimized, and energy escape and loss in the working process are avoided.
Rotor of the turbine disk: according to the working flow description of the working medium, the integrated structure and the function of the rotor module shown in fig. 3 are as follows, namely, a first working medium inlet 104 for connecting and intensively leading the working medium into the turbine blade 105; the second centrifugal turbine blade 105 is used for connecting the rotor cavity 100 with the bearing lantern ring structure and distributing working media into the rotor cavity to the guide air channel 106, the windward rotation direction of the turbine blade is synchronous with the rotor, the root part is axially communicated, and the working media are not influenced to penetrate to the rear stage turbine disk unit; thirdly, the guide air channel 106 is used for compressing and conveying working media to a main nozzle 108 formed by rotor movable blades 107 at the edge of the rotor; fourthly, the working medium is sprayed out from the main nozzle 108 in the opposite direction of the rotation of the rotor to obtain the reverse kinetic energy; fifthly, the working medium sprayed out of the main nozzle 108 is pressed back to the working medium through the stator blades 102, enters the air port 1112, is sprayed out through the air port 1113 connected with the working medium, is pressed back to the air port 1114 through the stator, is sprayed out through the air port 1115 connected with the working medium, and the energy is attenuated by doing work through the multiple energy composite air passages 111; sixthly, the composite air passage 111 is used for key parts for converting the working medium to roundabout work and energy step by step; seventh, the movable vane 107 is a profile component of the main nozzle 108 and the composite air passage 111, which is a main component for the expansion work of the working medium to bear the expansion tension, the radial inclination angle of the movable vane 107 is consistent with that of the stator vane 102, and the gap between the movable vane 107 and the stator vane 102 is the space for the expansion work of the working medium; eighthly, after the work is finished, the working medium allowance is discharged from the gas outlet 110 to the opposite direction of the rotation of the rotor; ninth, a double-layer bearing housing 112 for bearing installation and rotor cooling layout; tenth, a non-contact air seal ring 103 is arranged at the conjunction position of the rotor edge and the stator shell and used for reducing the escape of working media; eleventh, vent hole 109 is used for rotor heat dissipation assistance.
Adaptability of the turbine disk drive: in the application aspect of the turbine disk driving device, different devices have different matching requirements, as shown in fig. 9, a plurality of rotor examples with different powers are listed to match the corresponding devices; fig. 9 shows a large pattern a to a large pattern G of various types of turbine disks having the same diameter and different powers, arranged from large to small: the large sample diagram a of fig. 9 is a four-nozzle, multi-module combined connected mode, and is characterized by high output power, general maneuverability, suitability for large power generation, large ducted aircraft, ships, and the like, and if the diameters of the wheel discs are large (for example, more than one meter), nozzles and corresponding modules can be added to further increase working medium flux and thus increase power output; the B large sample diagram of FIG. 9 is a four-nozzle large aperture mode, and a single module with a large aperture ratio can be used for medium and small-sized equipment independently due to the fact that the power output of the single module is larger, and can also be driven by a large-aperture multi-module in a combined mode to be assembled on ultra-large-sized equipment; the rough drawing C of fig. 9 is a four-nozzle standard model, which is suitable for multi-module combined driving because indexes of various aspects of the wheel disc of the standard model are compromised, can respond to mobility variables while saving more energy when being equipped with a variable-diameter regulating valve, and is suitable for various mobile equipment, including strong mobility equipment such as aircrafts, ships, locomotives and the like; the large sample diagram D of FIG. 9 is a dual-nozzle, ultra-long composite airway model, general maneuverability, and applicability to energy-saving devices, and because the composite airway is longer and more graded, energy conversion is more sufficient, energy consumption is low; the turbine disk rotors of the following E, F, G large panel are all suitable for small-scale equipment, and E of the large panel of the figure 9 is a double-nozzle short composite air passage mode; FIG. 9 is a F plot of a dual orifice single layer circuitous airway pattern; FIG. 9 is a large panel G showing a simplified dual jet monolayer single counterplate pattern; the specific matching formula needs flexible matching according to the equipment requirements.
The layout of the composite air passage 111 is divided into two parts, namely two side air passages and a middle air passage, wherein the side air passages are large in section as shown in fig. 7, and are combined with the large in section as shown in fig. 8 of the middle air passage, the air passages are not communicated with each other in the projection drawing of the outline of the rotor, working media are sprayed out from a main orifice 108 of the middle air passage of the rotor, and are pressed against air passages 1112 at two sides of the rotor through a stator blade 102 to enter, then are sprayed out from a connected U-shaped air passage to a 1113 air port, and then enter through an air port 1114 of the middle air passage through the back pressure of the stator blade, and so on, the working media are pressed back between the middle air passage and the air passages at two sides through the stator blade to be switched back and; the sum of the sectional areas of the air passages at the two sides is equal to the sectional area of the middle air passage; the shape of the middle airway and the shape of the two airways are consistent, but the arrangement is asynchronous, for example, the beginning of the middle airway is parallel to the end of the two airways.
The reducing regulation control valve 207 is described as: the reducing regulation control valve 207 shown in fig. 2 is used for adjusting the variable of the working medium flowing into the turbine disc under different working conditions, and the intermediate value of the minimum flux and the maximum flux (fully open) is preset to be a controllable range, so that the minimum value of low-speed operation is maintained as the lower limit of the aperture of the bypass, and the bypass is not in a closed state. The O is in the full open state as in the large sample of FIG. 11, and I is in the minimum state; the adjusting valve 207 is implemented by an inner bracket 2072 through a connecting rod 2073 to rotate and adjust a valve piece 2074 to adjust the aperture of the duct according to the requirement, and manual intervention can be performed; valve disks operate under extreme operating conditions for long periods of time, requiring the use of high grade heat resistant materials such as cobalt or nickel based metals.
Centrifugal adaptive regulator valve 208 describes: the reducing valve 208 shown in fig. 2 is used to adjust the variable of the working medium flowing into the turbine disk under different working conditions, and the intermediate value between the minimum flux and the maximum flux (fully open) is preset as a controllable range, so as to maintain the minimum value of low-speed operation as the lower limit of the aperture of the bypass without a closed state. In FIG. 13, O is the fully open state, and I is the minimum value state; the inner support 2082 of the regulating valve 208 is used for supporting and mounting the valve sheet 2084 on the rotating shaft 2085, the elastic steel pressing sheet 2083 presses the valve sheet 2084 towards the circle center until the I big sample state of the figure 13-1 is a normal state, when the rotating speed is increased, the centrifugal force of the valve sheet 2084 is increased, the pressing sheet is ejected towards the outside direction of the circle center, and the aperture of the expanded duct is as the O big sample state of the figure 13-2; the self-adaptive regulating valve rotates synchronously with the turbine disc, manual intervention is not needed, and the self-adaptive regulating valve can be fixedly arranged in a closed cavity to simplify the structure; valve disks operate under extreme operating conditions for long periods of time, requiring the use of high grade heat resistant materials such as cobalt-based or nickel-based metals.
The specific scheme adopted by the invention in the aspect of improving the energy conversion rate is as follows: first, the sectional energy obtaining method, as shown in fig. 3, the working medium is ejected from the main nozzle 108, is back-pressed to the 1112 air port of the rotor through the stator vane 102, enters through the connected air passage to the 1113 air port, is back-pressed to 1114 air port through the stator vane, is ejected from 1115 air port through the connected air passage, is back-pressed to 1116 air port through the stator vane, is ejected from 1117 air port through the connected air passage, enters through 1118 air port through the stator back-pressure, is ejected from 1119 through the connected air passage, is back-pressed to 1120 air port through the stator vane, at this time, the decay is finished, the residual working medium is ejected out of the cavity of the rotor from the exhaust port 110 in the opposite direction of the direction V through the connected air passage, the stage setting of work doing work decay acts on the refined; secondly, a reverse energy obtaining method, as indicated in fig. 8, the working medium of the main nozzle 108 is sprayed to the opposite direction of the rotation direction V of the rotor, the air port 1111 beside is used for expanding the main nozzle 108, the force for buffering and absorbing the back pressure of the stator is taken as the first stage of working medium expansion work, the design that the expanded air port is arranged at one side behind the main nozzle is in an isolated state without being communicated with other air passages, and the purpose is to keep the energy concentration of the working medium of the main nozzle close to the operation front end, press the working medium to the rear, namely the reverse direction of the rotation direction V, and perform gradual work, attenuation and discharge; the exhaust of the exhaust port 110 is in the opposite direction of the rotating direction V, and the nozzle rotates along with the rotor, so that the moving speed of the discharged surplus working medium is obviously slowed down relative to the static stator 101 to present an overflow state, and compared with the gushing state of axial flow type inclination spraying pressure of a turbine, the dynamic discharge mode can obviously reduce the flowing speed of the working medium so as to convert more energy to improve the direct output efficiency of the equipment.
The technical scheme adopted by the invention in the aspect of obtaining the lifting torque of the rotor is as follows: first, centralized redistribution, as shown in fig. 8, working medium is led in from a cavity inlet 104 in a centralized manner, and the working medium is redistributed to a main nozzle 108 of a rotor edge area with the largest working radius by using a diversion channel 106 in a turbine disc structure to release and work, so that the maximum torque radius is obtained; secondly, the stressed section for applying work is designed at the tangential position of the circular edge of the turbine disc, and a space with a radial tangent plane opposite relation is formed between the blade gap of the rotor movable blade 107 and the blade gap of the stator blade 102 as guided by fig. 7, so that a working medium can expand to apply work to press the rotor blade to rotate towards the direction V, and a torsion force is directly generated; compared with a work doing method for obtaining rotating torque force by a turbine axial flow type pressure blowing beveling blade, the method is more direct in a torque force generation mode.
The technical scheme adopted by the invention in the aspect of improving the energy loss at low speed is as follows: the energy consumption of the gas turbine during idling also reaches 60-80% of the full working condition, and the turbine disk driving device of the invention is characterized in that a reducing valve is arranged between the turbine disk and the turbine disk at the front end of the inlet 104 of the cavity of the turbine disk, such as 207 and 208 positions shown in figure 2; when the equipment runs at a non-uniform speed, the variable-diameter valve can adjust the opening degree of the valve according to the speed and the requirement, so that the flux of the working medium is changed; when the equipment runs at idle speed, the reducing valve is contracted to a preset rated minimum flux state without a closing state, such as a state of 1076 position indicated by figures 11-1 and 11-2 and a state of 1086 position indicated by figures 13-1 and 13-2, so as to maintain the minimum running energy of the turbine disc, and the dynamic flow control mode can reduce the power consumption of the combustion engine at low speed or idle speed.
The technical scheme adopted by the invention in the aspect of maneuvering response is as follows: the working process of the turbine disk driving device is shown in fig. 8, working medium enters the cavity in a centralized manner at the cavity inlet 104, is distributed and guided to the edge area of the rotor with the largest torsion radius through the air passage 106, is sprayed out from the nozzle 108, is forced to be pressed into the composite passage 111 with all energy levels and relatively shielded, and is finally discharged from the tail exhaust port 110; in the process, the diameter ratio of the path through which the working medium flows is longer and the working medium is surrounded, so that the working is sufficient, the energy escape amount is relatively less, and the working medium is not easy to stall in a low-speed state, so that vector output can be relatively kept even if the variable of the working condition is large, and effective maneuvering response is guaranteed.
The technical scheme adopted by the invention in the aspect of cost is as follows: firstly, the stator and rotor layouts of the turbine disc 1 are in radial corresponding fit, as shown in fig. 4-1, 4-2 and 4-3, a heat flow path is lengthened through an air passage 106 to avoid that the blades of the stator blades 102 and the blades of the rotor blades 107 bear overheated working media which are nearly directly injected, and secondly, the radius range of the stator is compressed outwards from the circle center, so that a longer torsion radius is reserved in an acting area to increase torque, meanwhile, the expansion use area of the stator blades is reduced, and the interface of the external heat dissipation layout is increased; thirdly, the working medium is directly born and back-pressed by the stator when being sprayed out from the main nozzle, so that the blades of the main nozzle of the rotor and the blades of the stator bear the most severe working condition environment, but the sectional area range of the stator is reduced based on the intermittent heating of the stator and the layout modification of the stator by the first term and the second term; fourthly, most parts of the outer surface of the rotor disc needing heat dissipation are placed in a normal temperature area, and the layout of a cooling system is simple and convenient; compared with a turbine, the basic materials of the rotor and the stator of the turbine disk can slightly reduce the heat-resisting grade and can also achieve better cooling effect; the rotor blade does work in stages, the severity of the working condition decreases gradually from the main nozzle position, and the use amount of high-value materials can be correspondingly reduced, so that the manufacturing cost is reduced, and the service life of equipment is prolonged.
While the above description is only illustrative of the present invention, it should be noted that the turbine disk drive apparatus as described herein may also be used in other systems such as, but not limited to, steam engines, compressed air locomotives, pneumatic engineering tools, and the like. Therefore, the protection scope of the present invention should be subject to the protection scope and core principle logic defined by the claims.
Claims (10)
1. A turbine disk drive, characterized by: the turbine disc mechanism (1) is fixedly arranged on the transmission shaft mechanism (2); the transmission shaft mechanism (2) is arranged in the casing system (3) through a bearing; the casing system (3) is fixed on a bracket of the supporting system (4);
the turbine disc mechanism comprises more than one turbine disc, each turbine disc comprises a stator assembly and a rotor assembly, the stator assembly comprises a stator shell (101) and a circle of stator vanes (102) arranged in an inner cavity of the stator shell (101) in a surrounding mode;
the rotor assembly comprises a rotor disc (100), a non-contact type air seal ring (103) is arranged at the joint of the outer part of the rotor disc and a stator shell, more than one group of composite air passage structures are arranged along the edge of the outer circle of the rotor disc (100), a working medium inlet (104) is arranged at the position, close to the working medium output side, in the center of the circle center of the rotor disc (100), a bearing ring (113) is arranged in the middle of the working medium inlet, centrifugal turbine blades (105) are connected around the bearing ring (113) and used for structurally connecting the bearing ring and a turbine disc main body and centrally leading in working medium to the centrifugal turbine blades, and a centrifugal diversion air passage (106) is arranged in the rotor disc (100) corresponding; the output end of the centrifugal flow guide air passage (106) is communicated with the air inlet end of the composite air passage at the axial side by side position through a stator gap, the centrifugal turbine blade (105) is used for connecting the rotor disc (100) and the bearing lantern ring and distributing working media to the centrifugal flow guide air passage (106) from the inside of the rotor disc (100), the windward rotating direction of the centrifugal turbine blade (105) is synchronous with the rotor, and the root part is axially through; the centrifugal flow guide air passage (106) is used for compressing and conveying working media to the main nozzle (108), the nozzle shape of the centrifugal flow guide air passage is formed by surrounding a rotor movable vane structure, the working media are sprayed out from the main nozzle (108) to the opposite direction of the rotating direction to obtain reverse kinetic energy, and an expansion air port (1111) is further arranged on the rotating shaft disc positioned on one side of the adjacent back of the main nozzle (108); each group of composite air passage structures are also provided with an air outlet (110), when the work is finished, the working medium allowance is discharged from the air outlet (110) to the opposite direction of rotation, and the middle of the rotor disc (100) is provided with more than zero ventilation holes (109) for heat dissipation, which are increased or decreased according to the requirement of a heat dissipation mode.
2. The turbine disk drive of claim 1, wherein: the composite air channel structure comprises more than one expansion air port (1111), a main air port (108), a first air inlet (1112) arranged side by side with the main air port (108), a first air jet (1113) communicated with the first air inlet (1112) through a composite air channel (111), a second air inlet (1114) arranged side by side with the first air jet (1113), a second air jet (1115) communicated with the second air inlet (1114) through the composite air channel (111), a third air inlet (1116) arranged side by side with the second air jet (1115), a third air jet (1117) communicated with the third air inlet (1116) through the composite air channel, a fourth air inlet (1118) arranged side by side with the third air jet (1117), a fourth air jet (1119) communicated with the fourth air inlet (1118) through the composite air channel, and a fifth air inlet (1120) arranged side by side with the fourth air jet (1119), the output end of the fifth air inlet (1120) is communicated with the exhaust port; the number of stages of the composite air passage is increased or decreased according to needs.
3. The turbine disk drive of claim 1, wherein: the radial inclination angle of the rotor movable blade (107) is consistent with that of the stator blade (102), and the gap between the rotor movable blade and the stator blade is a space for the working medium to do work through expansion.
4. The turbine disk drive of claim 1, wherein: a non-contact type air seal ring (103) is arranged at the joint of the rotor disc (100) and the stator shell (101).
5. The turbine disk drive of claim 1, wherein: the transmission shaft mechanism comprises a rotor air inlet and outlet connecting ring (201), a sealing telescopic ring (202), a rotor air inlet sealing cover (203), a power output end (204), a high-speed turbine disc air sealing bearing ring (205), a double-layer bearing ring (206), a reducing adjusting control valve (207), a centrifugal reducing self-adapting adjusting valve (208) and a turbine connecting bearing (209), wherein the turbine disc comprises a low-speed turbine disc and a high-speed turbine disc, the double-layer bearing ring (206) is used for connecting a casing connecting port and installing a bearing of a main transmission shaft and a compressor high-speed turbine transmission shaft, the rotor air inlet and outlet connecting ring (201) is used for connecting a working medium inlet and outlet and interconnecting the turbine disc and the turbine disc, the sealing telescopic ring (202) is made of a ductile metal material and used for strong pressure buffering, the high-speed turbine transmission shaft is connected with a compressor driving wheel and used for driving the compressor to operate, the air inlet and outlet connecting ring (201) is used for connecting the air inlet and outlet of the turbine disk and the related interface, and the rotor air inlet sealing cover (203) is used for sealing the air channel at the tail end of the turbine disk module.
6. The turbine disk drive of claim 5, wherein: the variable-diameter adjusting control valve comprises a control valve outer frame (2071), a control valve inner support (2072), a control valve pull rod (2073), a control valve plate (2074) and a control valve rotating shaft (2075); the control valve inner supports (2072) are arranged into two inner and outer supports which are arranged in the middle of the control valve outer frame, the two control valve inner supports are arranged in an inner and outer ring structure and are connected through more than one control valve pull rod, two ends of the control valve pull rod are respectively connected with the two control valve inner supports through a control valve rotating shaft, and a control valve sheet is arranged in the middle of the control valve inner support of the inner ring;
the centrifugal diameter-variable self-adaptive regulating valve comprises a regulating valve outer frame (2081), a regulating valve inner support (2082), a regulating valve elastic pressing sheet (2083), a regulating valve sheet (2084) and a regulating valve rotating shaft (2085), wherein the regulating valve inner support is arranged at the middle position of the regulating valve outer frame, the regulating valve sheet is connected with the regulating valve inner support through the regulating valve rotating shaft, the regulating valve elastic pressing sheet presses the regulating valve sheet (2084) to the inside of a circle center, one end of the regulating valve elastic pressing sheet is elastically connected with the inner side surface of the regulating valve outer frame.
7. The turbine disk drive of claim 1, wherein: the casing system comprises a shell (301), an outer duct (302), a casing framework (303), a main transmission shaft bearing (304), a high-pressure vortex plate connecting compressor bearing (305), an exhaust hole (306) and a high-pressure turbine bearing (307), wherein the shell is divided into an upper part and a lower part, a stator shell and stator blades are arranged in the shell, the main transmission shaft bearing (304) is connected with the shell through the casing framework (303), the outer duct is formed between the casing frameworks, the output end of a turbine disc exhaust hole (110) is communicated with the exhaust hole (306), the exhaust hole is communicated with the outer duct, the length of the exhaust hole (306) is equal to the distance between two turbine discs, and the width is 0.5 of 36 minutes of the circumference, namely, each hole is 5 degrees, the width of the hole is equal to the width of the interval, the residual gas is discharged from the exhaust hole (110) of the turbine disc and then drives the residual working medium to be discharged outwards by centrifugal force, and the residual working medium is discharged to an outer duct through the exhaust hole (306) on the inner wall of the casing.
8. The turbine disk drive of claim 1, wherein: the supporting system comprises a base (401) and a support (402), wherein the base (401) is arranged at the bottom of the support (402), and the support (402) is used for installing a shell of the supporting system.
9. The turbine disk drive of claim 1, wherein: the composite air passage (111) comprises two parts of two side air passages and a middle air passage, working media are sprayed out from a main air passage (108) of the middle air passage of the rotor and enter through the stator blades to counter pressure the air passage openings on the two sides of the rotor, and the sum of the sectional areas of the two side air passages is larger than or equal to the sectional area of the middle air passage.
10. A gas turbine, characterized by: a gas turbine equipped with the turbine disk drive device as claimed in claims 1 to 9.
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| CN202011233644.7A CN112324570A (en) | 2020-11-06 | 2020-11-06 | Turbine disk driving device and gas turbine using same |
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| CN202011233644.7A CN112324570A (en) | 2020-11-06 | 2020-11-06 | Turbine disk driving device and gas turbine using same |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
| CN114708783A (en) * | 2022-04-12 | 2022-07-05 | 西北工业大学 | Detachable model and method for aircraft engine high-pressure compressor for teaching |
| CN117108374A (en) * | 2023-10-20 | 2023-11-24 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101349197A (en) * | 2007-07-22 | 2009-01-21 | 蔡盛龙 | Contrarotating rotary spraying engine |
| WO2009065416A1 (en) * | 2007-11-20 | 2009-05-28 | Abdelghani Benhama | Turbomachine having multi-stage turbine discs |
| CN103306736A (en) * | 2012-04-30 | 2013-09-18 | 王政玉 | Power turbine and power machine of the power turbine |
| CN103939148A (en) * | 2014-04-28 | 2014-07-23 | 哈尔滨工程大学 | Radial flow turbine with multiple splitter blades |
| KR20150086590A (en) * | 2014-01-20 | 2015-07-29 | 이재본 | Centrifugal multi-stage turbine combined with original through-hole impeller |
| CN110249113A (en) * | 2016-11-25 | 2019-09-17 | 索科普哈应用研究产品商业化公司基因科学Sec | Refractory ceramics rotating turbomachinery |
-
2020
- 2020-11-06 CN CN202011233644.7A patent/CN112324570A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101349197A (en) * | 2007-07-22 | 2009-01-21 | 蔡盛龙 | Contrarotating rotary spraying engine |
| WO2009065416A1 (en) * | 2007-11-20 | 2009-05-28 | Abdelghani Benhama | Turbomachine having multi-stage turbine discs |
| CN103306736A (en) * | 2012-04-30 | 2013-09-18 | 王政玉 | Power turbine and power machine of the power turbine |
| KR20150086590A (en) * | 2014-01-20 | 2015-07-29 | 이재본 | Centrifugal multi-stage turbine combined with original through-hole impeller |
| CN103939148A (en) * | 2014-04-28 | 2014-07-23 | 哈尔滨工程大学 | Radial flow turbine with multiple splitter blades |
| CN110249113A (en) * | 2016-11-25 | 2019-09-17 | 索科普哈应用研究产品商业化公司基因科学Sec | Refractory ceramics rotating turbomachinery |
Non-Patent Citations (1)
| Title |
|---|
| 周松等: "《内燃机工作过程仿真技术》", 31 August 2012, 北京航空航天大学出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
| CN114708783A (en) * | 2022-04-12 | 2022-07-05 | 西北工业大学 | Detachable model and method for aircraft engine high-pressure compressor for teaching |
| CN117108374A (en) * | 2023-10-20 | 2023-11-24 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
| CN117108374B (en) * | 2023-10-20 | 2023-12-15 | 中国航发沈阳发动机研究所 | Three-cavity separation type integrated bearing casing combined structure |
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