Low-conductivity multifunctional counter-rotating turbine structure

Abstract

The present application belongs to the technical field of small gas turbine engine, and discloses a low-guide-free multifunctional counter-rotating turbine structure. The high-pressure turbine rotor unit body of the low-guide-free multifunctional counter-rotating turbine structure converts the high-temperature and high-pressure gas flow from the main flow into the kinetic energy of the high-pressure rotor rotating counterclockwise along the direction, discharges the high-temperature and high-pressure gas flow along the tangential direction, and then enters the low-pressure turbine rotor unit body through the low-guide-free multifunctional inter-stage support structure, drives the low-pressure rotor blade to rotate clockwise along the direction, and realizes the reverse rotation of the high-pressure rotor blade and the low-pressure rotor blade. Meanwhile, the low-guide-free multifunctional inter-stage support structure is provided with double-bearing multi-oil sliding pipelines. The low-guide-free multifunctional counter-rotating turbine can meet the design requirements of high-performance gas turbine engine for high-load and high-efficiency turbine, solve the technical problems of variable mass distribution, variable stiffness, double elastic damping, wide frequency and multifunctional low-guide-free counter-rotating turbine integrated design, and has engineering practical value.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of small gas turbine engines, and particularly relates to a low-guide-vane-free multifunctional counter-rotating turbine structure. BACKGROUND

[0002] The turbine is one of the core components of the gas turbine power device, is a turbomachinery for converting the chemical energy of high-temperature and high-pressure gas into kinetic energy and mechanical energy, and works in a complex and severe environment of high temperature, high pressure and high speed for a long time. The environmental adaptability directly determines the technical advancement and safety and reliability of the turbine to a certain extent.

[0003] The counter-rotating turbine is composed of two rotors arranged in front and back in opposite directions. Compared with the conventional turbine, the counter-rotating turbine has obvious advantages in engine aerodynamic performance, cooling design, engine structure and improvement of aircraft maneuverability. However, since the rotation directions of the high-pressure rotor and the low-pressure rotor in the counter-rotating turbine are opposite, the relative rotation speed of the two rotors is doubled, which makes the rotor system more sensitive to the dynamic response of the unbalanced inertia moment, which brings great challenges to the safe, stable and reliable work of the rotor. Therefore, designing a scientific and reasonable low-guide-vane-free counter-rotating turbine structure is one of the key technologies for determining whether the counter-rotating mode can be realized, and is also one of the core technologies for the structure design of the counter-rotating turbine.

[0004] At present, it is urgent to develop a low-guide-vane-free multifunctional counter-rotating turbine structure. SUMMARY

[0005] The application aims to solve the technical problem of providing a low-guide-vane-free multifunctional counter-rotating turbine structure to overcome the defects of the prior art.

[0006] The low-guide-vane-free multifunctional counter-rotating turbine structure of the application is composed of a high-pressure turbine rotor unit body, a low-pressure turbine rotor unit body, a low-guide-vane-free multifunctional inter-stage support structure and a double-bearing multi-oil-pipeline integrated structure.

[0007] The high-pressure turbine rotor unit body converts the high-temperature and high-pressure gas flow from the main flow into the kinetic energy of the high-pressure rotor rotating counterclockwise along the direction, and discharges the high-temperature and high-pressure gas flow along the circumferential tangential direction, and then enters the low-pressure turbine rotor unit body through the low-guide-vane-free multifunctional inter-stage support structure, drives the low-pressure rotor blade to rotate clockwise along the direction, and realizes the reverse rotation of the high-pressure rotor blade and the low-pressure rotor blade; at the same time, the double-bearing multi-oil-pipeline is arranged on the low-guide-vane-free multifunctional inter-stage support structure.

[0008] Wherein, the high-pressure turbine rotor unit body is an integral blade disc type high-pressure turbine rotor unit body, the low-pressure turbine rotor unit body is an integral blade disc type low-pressure turbine rotor unit body; the low-guide multi-functional inter-stage support structure is a variable stiffness and strong damping inter-stage support structure without a low-pressure turbine guide vane, and the low-guide multi-functional inter-stage support structure is provided with an outer casing with honeycomb slot type sealing; the double-bearing multi-sliding oil pipeline is an oil inlet and return pipeline passing through the No. 1 bearing inner sleeve and the No. 2 bearing inner sleeve.

[0009] Further, the high-pressure turbine rotor unit body is composed of high-pressure rotor blades with a blade profile T, a high-pressure disc body, a front sealing runway, a No. 1 bearing inner sleeve and an axial compression nut; the high-pressure rotor blades and the high-pressure disc body are in an integral structure, the front end surface of the high-pressure disc body is provided with sealing grate O, balance material taking block K and upstream piece connecting flange M; wherein the upstream piece is connected by bolt connection friction torque and axial limiting through the flange M, and is radially centered through the cylindrical surface A; the rear end shaft neck of the high-pressure disc body is provided with an air flow path P, the front sealing runway and the No. 1 bearing inner sleeve are installed, and the axial compression nut is used for axial fixation.

[0010] Further, the low-pressure turbine rotor unit body is composed of low-pressure rotor blades with sawtooth crown S blade profile G, a low-pressure disc body, a transition shaft, a low-pressure shaft, a rear sealing runway, an oil throwing disc, a No. 2 bearing inner sleeve and a compression nut; the low-pressure rotor blades and the low-pressure disc body are in an integral structure, the low-pressure disc body is designed with balance material taking block Y, rear shaft neck air vent X and rear end surface connecting flange Q, and is bolted and connected by friction torque and axially limited through the flange Q and the transition shaft, the transition shaft and the low-pressure shaft are connected by spline F torque, and are tightly and serially installed with the rear sealing runway, the oil throwing disc and the No. 2 bearing inner sleeve in the axial direction, and are tightened and constrained by the compression nut at the axial rear end; the middle cylindrical surface of the low-pressure shaft is designed with multiple grate N for air sealing to seal the No. 1 bearing cavity and the No. 2 bearing cavity, so as to prevent oil leakage.

[0011] Further, the low-guide multi-functional inter-stage support structure is composed of an outer casing, an outer ring, a transition support plate, a support body, a web, a front sealing body, a No. 1 bearing body, an adjusting ring, a No. 2 bearing body, a rear sealing body and an oil inlet and return pipeline; wherein the casing and the outer ring are installed and radially limited through the C cylindrical surface, the outer casing is provided with a boss J1, and the boss J1 is provided with an installation hole J2 for installing the oil inlet and return pipeline and being fixed through the pressing plate J3; the cross section of the transition support plate is oval, including three support plates distributed along the circumference and mutually distributed at 120°, the central axes of the uppermost support plate and the lowermost support plate are provided with through holes, the oil inlet and return pipeline is installed in the through holes, the rear end of the transition support plate is bolted and connected with the support body to transfer load and is centered through the radial stop, the front end of the transition support plate is constrained and limited through the buckle E and the web; the support body and the web are bolted at the H surface, and the front sealing body, the No. 1 bearing body and the adjusting ring are axially compressed and constrained; the rear end of the support body is installed with the No. 2 bearing body and the rear sealing body, and the support body and the oil inlet and return pipeline are fixed and sealed through the insertion hole D thread.

[0012] The low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application adopts multi-functional integrated design, and has the following characteristics:

[0013] First, the aerodynamic design of the low-pressure turbine guide-free structure is adopted, and the high-pressure turbine rotor and the low-pressure turbine rotor are realized in reverse rotation.

[0014] Second, the integrated design of variable mass distribution, variable stiffness, double elastic damping and wide frequency is adopted, and by changing the supporting structure form, optimizing the contact mode, designing the elastic damping and other measures, the stiffness of the supporting mechanism is changed, the damping of the supporting system is improved, and the vibration response of the rotor is reduced, and the variable stiffness and strong damping inter-stage supporting structure of the low-pressure turbine guide-free structure is established.

[0015] Third, the double-bearing seat shared supporting structure is adopted to ensure the isolation of the vibration signals between the supporting points, and to reduce the coupling response of the vibration between the high-pressure rotor and the low-pressure rotor, and the oil inlet pipeline is arranged directly above the supporting structure, and the oil return pipeline, the oil return groove and the oil injection nozzle are arranged directly below the supporting structure, and the integrated double-bearing multi-oil pipeline structure is established.

[0016] The low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application can meet the design requirements of high-performance gas turbine engines for high-load and high-efficiency turbines, improve the turbine performance, function and structural strength, solve the technical problems of variable mass distribution, variable stiffness, double elastic damping, wide frequency and multi-functional low-guide counter-rotating turbine integrated design, break through the technical bottleneck of advanced high-performance gas turbine engines, and have engineering practical value. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a schematic diagram of the low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application;

[0018] Figure 2 It is a schematic diagram of the high-pressure turbine rotor unit body structure in the low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application;

[0019] Figure 3 It is a schematic diagram of the low-pressure turbine rotor unit body structure in the low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application;

[0020] Figure 4 It is a schematic diagram of the low-pressure turbine guide-free multi-functional inter-stage supporting structure in the low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application.

[0021] Figure 5 It is a schematic diagram of the low-pressure turbine guide-free multi-functional inter-stage supporting structure in the low-pressure turbine guide-free multi-functional counter-rotating turbine structure of the present application.

[0022] In the figure, 1. high-pressure turbine rotor unit body; 2. low-pressure turbine rotor unit body; 3. low-pressure turbine guide-free multi-functional inter-stage supporting structure;

[0023] 101. high pressure rotor blade; 102. high pressure disk body; 103. front sealing track; 104. No. 1 bearing inner sleeve; 105. axial compression nut;

[0024] 201. low pressure rotor blade; 202. low pressure disk body; 203. transition shaft; 204. low pressure shaft; 205. rear sealing track; 206. oil throwing disc; 207. No. 2 bearing inner sleeve; 208. compression nut;

[0025] 301. outer casing; 302. outer ring; 303. transition support plate; 304. support body; 305. web; 306. front sealing body; 307. No. 1 bearing body; 308. adjusting ring; 309. No. 2 bearing body; 3010. rear sealing body; 3011. oil feeding and returning pipe. DETAILED DESCRIPTION

[0026] The present application will be described in detail below with reference to the accompanying drawings and examples.

[0027] As shown in the drawing, the low-guide-vane-free multifunctional counter-rotating turbine structure of the present embodiment is composed of a high pressure turbine rotor unit body 1, a low pressure turbine rotor unit body 2, a low-guide-vane-free multifunctional inter-stage support structure 3, and a double-bearing multi-oil-piping integrated structure 4. Figures 1-5 The high pressure turbine rotor unit body 1 converts the high temperature and high pressure gas flow from the main flow into the kinetic energy of the high pressure rotor rotating counterclockwise in the forward direction through the high pressure rotor blade 101, and discharges the high temperature and high pressure gas flow in the circumferential tangential direction, and then enters the low pressure turbine rotor unit body 2 through the low-guide-vane-free multifunctional inter-stage support structure 3, drives the low pressure rotor blade 201 to rotate clockwise in the forward direction, and realizes the reverse rotation of the high pressure rotor blade 101 and the low pressure rotor blade 201; at the same time, the low-guide-vane-free multifunctional inter-stage support structure 3 is provided with a double-bearing multi-oil-piping.

[0028] The high pressure turbine rotor unit body 1 is an integral blade disk type high pressure turbine rotor unit body, and the low pressure turbine rotor unit body 2 is an integral blade disk type low pressure turbine rotor unit body; the low-guide-vane-free multifunctional inter-stage support structure 3 is a low pressure turbine guide vane-free variable stiffness strong damping inter-stage support structure, and the outer casing 301 with honeycomb groove sealing is arranged in the low-guide-vane-free multifunctional inter-stage support structure 3; the double-bearing multi-oil-piping is an oil feeding and returning pipe passing through the No. 1 bearing inner sleeve 104 and the No. 2 bearing inner sleeve 207.

[0029] Further, as shown in the drawing, the low-guide-vane-free multifunctional counter-rotating turbine structure of the present embodiment is composed of a high pressure turbine rotor unit body 1, a low pressure turbine rotor unit body 2, a low-guide-vane-free multifunctional inter-stage support structure 3, and a double-bearing multi-oil-piping integrated structure 4.

[0030] Figure 2 ​As shown, the high-pressure turbine rotor unit body 1 is composed of high-pressure rotor blades 101 with blade profile T, high-pressure disc body 102, front sealing track 103, No. 1 bearing inner sleeve 104 and axial compression nut 105; the high-pressure rotor blades 101 and the high-pressure disc body 102 are of integral structure, the high-pressure disc body 102 is provided with sealing grate O, balance material taking block K and upstream piece connecting flange M on the front end face; among them, the upstream piece is connected by bolt of flange M to transmit friction torque and limit axially, and is centered radially by cylindrical surface A; the high-pressure disc body 102 is provided with air flow path P on the rear end shaft neck, installs front sealing track 103 and No. 1 bearing inner sleeve 104, and is axially fixed by axial compression nut 105.

[0031] Further, as shown in the figure, Figure 3 The low-pressure turbine rotor unit body 2 is composed of low-pressure rotor blades 201 with sawtooth crown S blade profile G, low-pressure disc body 202, transition shaft 203, low-pressure shaft 204, rear sealing track 205, oil throwing disc 206, No. 2 bearing inner sleeve 207 and compression nut 208; the low-pressure rotor blades 201 and the low-pressure disc body 202 are of integral structure, the low-pressure disc body 202 is designed with balance material taking block Y, rear shaft neck air passage X and rear end face connecting flange Q, and is connected by bolt of flange Q to transmit friction torque and limit axially, the transition shaft 203 and the low-pressure shaft 204 are connected by spline F to transmit torque, and are closely connected and assembled with rear sealing track 205, oil throwing disc 206 and No. 2 bearing inner sleeve 207 in axial direction, and are tightened and constrained by compression nut 208 at the rear end in axial direction; the low-pressure shaft 204 is designed with multiple grates N on the middle cylindrical surface, which is used for air sealing of No. 1 bearing cavity and No. 2 bearing cavity to prevent oil leakage.

[0032] Further, the low-guide multi-functional inter-stage supporting structure 3 is composed of outer casing 301, outer ring 302, transition supporting plate 303, supporting body 304, web plate 305, front sealing body 306, No. 1 bearing body 307, adjusting ring 308, No. 2 bearing body 309, rear sealing body 3010 and oil inlet and return pipe 3011; among them, as shown in the figure, Figure 4 The outer casing 301 and the outer ring 302 are installed and limited radially by C cylindrical surface, the outer casing 301 is provided with boss J1, and mounting hole J2 is arranged on the boss J1, which is used for mounting oil inlet and return pipe 3011 and fixing by pressing plate J3; as shown in the figure, Figure 5As shown, the cross section of the transition support plate 303 is oval, including three circumferentially distributed support plates, the center axes of the upper and lower support plates are provided with through holes, the oil return pipe 3011 is installed in the through holes, the rear end of the transition support plate 303 is bolted to the support body 304 to transfer load and is centered by the radial stop, the front end of the transition support plate 303 is constrained and limited by the buckle E; the support body 304 is bolted to the web 305 in the H plane, and the front sealing body 306, the first bearing body 307 and the adjusting ring 308 are axially compressed and constrained; the rear end of the support body 304 is provided with the second bearing body 309 and the rear sealing body 3010, and the support body 304 is fixed and sealed to the oil return pipe 3011 by the insertion hole D.

[0033] Although the embodiments of the present application have been disclosed as above, they are not limited to the applications listed in the specification and the embodiments, and all the features disclosed in the present application, or the steps in all the methods or processes disclosed in the present application, except for the mutually exclusive features and / or steps, can be combined in any manner, and the present application is not limited to specific details and the figures shown and described herein.

Claims

1. A low-conductivity multi-functional counter-rotating turbine structure, characterized by, The low-guide-free multifunctional counter-rotating turbine structure is composed of a high-pressure turbine rotor unit (1), a low-pressure turbine rotor unit (2), a low-guide-free multifunctional inter-stage support structure (3) and a double-bearing multi-oil-pipeline integrated structure (4); The high-pressure turbine rotor unit (1) converts the high-temperature and high-pressure gas flow from the main flow into the kinetic energy of the high-pressure rotor counterclockwise rotation through the high-pressure rotor blades (101), and discharges the high-temperature and high-pressure gas flow in the circumferential tangential direction, and then enters the low-pressure turbine rotor unit (2) through the low-guide-free multifunctional inter-stage support structure (3), drives the low-pressure rotor blades (201) to rotate clockwise along the direction, and realizes the reverse rotation of the high-pressure rotor blades (101) and the low-pressure rotor blades (201); meanwhile, the low-guide-free multifunctional inter-stage support structure (3) is provided with a double-bearing multi-oil-pipeline; The high-pressure turbine rotor unit (1) is an integral blade disc type high-pressure turbine rotor unit, the low-pressure turbine rotor unit (2) is an integral blade disc type low-pressure turbine rotor unit, the low-guide-free multifunctional inter-stage support structure (3) is a low-pressure turbine guide-free variable stiffness strong damping inter-stage support structure, the low-guide-free multifunctional inter-stage support structure (3) is provided with an outer casing (301) with a honeycomb groove type sealing, and the double-bearing multi-oil-pipeline is an oil inlet and return pipeline passing through a No. 1 bearing inner sleeve (104) and a No. 2 bearing inner sleeve (207); The low-guide-free multifunctional inter-stage support structure (3) is composed of an outer casing (301), an outer ring (302), a transition support plate (303), a support body (304), a web plate (305), a front sealing body (306), a No. 1 bearing body (307), an adjusting ring (308), a No. 2 bearing body (309), a rear sealing body (3010) and an oil inlet and return pipeline (3011); wherein the outer casing (301) is installed and radially limited through a C-cylinder surface with the outer ring (302), the outer casing (301) is provided with a boss J1, and the boss J1 is provided with a mounting hole J2 for mounting the oil inlet and return pipeline (3011) and fixing through a pressing plate J3; the cross section of the transition support plate (303) is oval, including three support plates distributed along the circumference and mutually distributed at an angle of 120°, through holes are arranged on the central axes of the upper support plate and the lower support plate, the oil inlet and return pipeline (3011) is mounted in the through holes, the rear end of the transition support plate (303) is bolted with the support body (304) to transfer the load and center through a radial stop, the front end of the transition support plate (303) is constrained and limited through a buckle E with the web plate (305); the support body (304) is bolted with the web plate (305) at an H surface, and the front sealing body (306), the No. 1 bearing body (307) and the adjusting ring (308) are axially pressed and constrained; the rear end of the support body (304) is mounted with the No. 2 bearing body (309) and the rear sealing body (3010), and the support body (304) is fixed and sealed with the oil inlet and return pipeline (3011) through a threaded insertion hole D.

2. The low-conductance multi-functional counter-rotating turbine structure according to claim 1, characterized by The high-pressure turbine rotor unit body (1) is composed of high-pressure turbine blade (101) with blade type T, high-pressure disc body (102), front sealing runway (103), No. 1 bearing inner sleeve (104) and axial compression nut (105); the high-pressure turbine blade (101) and the high-pressure disc body (102) are integrated structure, the high-pressure disc body (102) is provided with sealing grate O, balance material taking block K and upstream piece connecting flange M on the front end face; wherein the upstream piece is connected by bolt of the flange M to transmit friction torque and limit axially, and is centered radially by the cylindrical surface A; the high-pressure disc body (102) is provided with air flow path P on the rear end shaft neck, installs the front sealing runway (103) and No. 1 bearing inner sleeve (104), and is axially fixed by the axial compression nut (105).

3. The low conductance multi-functional counter-rotating turbine structure of claim 1, wherein, The low-pressure turbine rotor unit body (2) is composed of low-pressure turbine blade (201) with sawtooth crown S blade type G, low-pressure disc body (202), transition shaft (203), low-pressure shaft (204), rear sealing runway (205), oil throwing disc (206), No. 2 bearing inner sleeve (207) and compression nut (208); the low-pressure turbine blade (201) and the low-pressure disc body (202) are integrated structure, the low-pressure disc body (202) is designed with balance material taking block Y, rear shaft neck air hole X and rear end face connecting flange Q, and is connected by bolt of the flange Q to transmit friction torque and limit axially, the transition shaft (203) and the low-pressure shaft (204) are connected by spline F to transmit torque, and are closely connected and assembled with the rear sealing runway (205), the oil throwing disc (206) and No. 2 bearing inner sleeve (207) in the axial direction, and are constrained by the compression nut (208) at the rear end in the axial direction; the low-pressure shaft (204) is designed with multiple grates N on the middle cylindrical surface, which is used for air sealing No. 1 bearing cavity and No. 2 bearing cavity to prevent oil leakage.

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