CN-120042652-B - Prerotation pressurizing inclined sealing lip structure

Abstract

The invention discloses a pre-rotation pressurizing inclined sealing lip structure, relates to the technical field of high-temperature component turbines of aeroengines, and solves the problems that sealing gas in the prior art disturbs main flow gas, loses pneumatic performance of blades and gas backflow. The invention discloses a rotor, which is characterized in that an L-shaped bulge is arranged at the end part of a rotor rim of the rotor, which faces to a stator, an L-shaped groove is arranged at the end part of the stator rim of the rotor, which faces to the rotor, a gas flow channel is arranged between the L-shaped bulge and the L-shaped groove, and an outlet of the gas flow channel faces to the blade root position of a turbine movable blade. According to the invention, through structural modification of the axial gap at the rim of the turbine rotor and stator, certain guiding, steering and pressurizing effects are carried out on the sealing gas, the circumferential speed difference and the flow angle difference of the sealing gas and the main flow gas are reduced, the outlet pressure of the sealing gas is increased, the gas backflow phenomenon is reduced, and meanwhile, a certain cooling effect can be achieved on the root of the blade.

Inventors

• LUO LEI
• DU WEI
• SHANG YUKAI
• YAN HAN

Assignees

• 哈尔滨工业大学
• 哈工大苏州研究院

Dates

Publication Date

20260508

Application Date

20250325

Claims (4)

1. 1. The pre-rotation pressurizing inclined sealing lip structure is characterized by comprising a stator, a rotor, a turbine shaft (3) and a main flow channel (9), wherein the stator and the rotor are arranged in the main flow channel (9), the rotor is sleeved on the turbine shaft (3), an L-shaped bulge (10) is arranged at the end part of a rotor rim (2) of the rotor, which faces the stator, an L-shaped groove (5) is arranged at the end part of a stator rim (1), which faces the rotor, of the stator, a gas flow channel is arranged between the L-shaped bulge (10) and the L-shaped groove (5), the outlet of the gas flow channel faces the blade root position of a turbine movable blade (11), a plurality of gradually-expanding torsion grooves (6) are arranged on the L-shaped groove (5), the gradually-expanding torsion grooves (6) are arranged along a stacking curve (7), and the sectional area of the gradually-expanding torsion grooves (6) gradually increases from the starting point of the stacking curve (7) to the end point of the stacking curve (8); the stacking curve (7) is twisted along the circumferential direction, and the included angle between the tangent line at the end point (8) of the stacking curve and the circumferential direction is 44 degrees.
2. 2. The pre-rotation pressurizing inclined sealing lip structure according to claim 1, wherein an included angle between the long side of the L-shaped groove (5) and the axis of the turbine shaft (3) is 25 degrees.
3. 3. The pre-rotation pressurizing inclined sealing lip structure according to claim 1, wherein the cross section of the divergent torsion groove (6) is rectangular.
4. 4. The pre-rotation pressurizing inclined sealing lip structure according to claim 1, wherein the number of the divergent torsion grooves (6) is an integer multiple of the number of turbine blades (11).

Description

Prerotation pressurizing inclined sealing lip structure Technical Field The invention relates to the technical field of high-temperature part turbines of aeroengines, in particular to a pre-rotation pressurizing inclined sealing lip structure. Background The turbine of the aeroengine consists of a static part and a rotating part, wherein the turbine guider is the static part, the turbine rotor is the rotating part, and the static part and the rotating part are in direct contact with the high-temperature main flow gas. An axial gap is necessarily present between the rotating component and the static component, an annular cavity is present between the moving component and the static component, which is called a turbine disc cavity, in order to prevent high-temperature fuel gas in the main flow channel from flowing backward and invading between the turbine disc cavities, high-pressure low-temperature gas needs to be led out of the compressor and is led into the turbine disc cavity as sealing gas, and then the sealing gas is discharged into the main flow channel through a sealing lip, so that the turbine disc is protected from being corroded by high temperature fuel gas, and the gas film cooling can be carried out on the root parts and the lower end walls of the turbine blades. The introduction of sealing gas can cool and protect the turbine disc cavity and the blade root, but the flow form of main flow gas is also affected to some extent, the circumferential speed difference and the flow angle difference between the sealing outflow and the main flow can generate viscous shear, and the flow form of the main flow gas is disturbed, so that the aerodynamic performance of the turbine is reduced. The relative motion between the dynamic blade and the static blade can generate the phenomenon of uneven circumferential pressure distribution, so that the partial main flow gas pressure of the rim is larger than the sealing gas pressure in the turbine disc cavity, and the gas backflow phenomenon occurs. The sealing gas disturbs the main flow gas, the pneumatic performance of the lost blade, the reverse flow of the fuel gas and other problems, so that the overall efficiency and the service life of the aeroengine are affected, and the sealing gas has very important significance in solving the problems. Disclosure of Invention The invention provides a pre-rotation pressurizing inclined sealing lip structure for solving the problems that sealing gas in the prior art disturbs main flow gas, loses pneumatic performance of blades, and fuel gas flows backwards. According to the invention, through structural modification of the axial gap at the rim of the turbine rotor and stator, certain guiding, steering and pressurizing effects are carried out on the sealing gas, the circumferential speed difference and the flow angle difference of the sealing gas and the main flow gas are reduced, the outlet pressure of the sealing gas is increased, the gas backflow phenomenon is reduced, and meanwhile, a certain cooling effect can be achieved on the root of the blade. The invention provides a pre-rotation pressurizing inclined sealing lip structure, which specifically comprises a stator, a rotor, a turbine shaft and a main flow channel, wherein the stator and the rotor are arranged in the main flow channel, the rotor is sleeved on the turbine shaft, an L-shaped bulge is arranged at the end part of a rotor rim of the rotor, which faces the stator, an L-shaped groove is arranged at the end part of the stator rim, which faces the rotor, of the stator, a gas flow channel is arranged between the L-shaped bulge and the L-shaped groove, and an outlet of the gas flow channel faces the blade root position of a turbine movable blade. Further, the included angle between the long side of the L-shaped groove and the axis of the turbine shaft is 25 degrees. Further, a plurality of gradually-expanding twisted grooves are formed in the L-shaped groove, the gradually-expanding twisted grooves are arranged along the stacking curve, and the sectional area of the gradually-expanding twisted grooves gradually increases from the starting point of the stacking curve to the end point of the stacking curve. Still further, the stacking curve is distorted in the circumferential direction. Further, the included angle between the tangent line at the end point of the stacking curve and the circumferential direction is 44 degrees. Further, the cross-sectional shape of the diverging twist groove is rectangular. Further, the number of the gradually expanding twisted grooves is an integer multiple of the number of the turbine blades. The pre-rotation pressurizing inclined sealing lip structure has the beneficial effects that: (1) The lip structure is composed of a turbine rotor rim part, the axial clearance at the turbine rotor rim part is subjected to structural modification, the sealing gas is subjected to certain guiding, steering and pressurizing effects, the circumferenti