CN112459851A

CN112459851A - Turbine movable blade cooling air supercharging device

Info

Publication number: CN112459851A
Application number: CN202011164899.2A
Authority: CN
Inventors: 林枫; 刘文文; 刘庆鹤; 李宗全; 张立超; 何全章
Original assignee: Csic Longjiang Gh Turbine Co ltd
Current assignee: Csic Longjiang Gh Turbine Co ltd
Priority date: 2020-10-27
Filing date: 2020-10-27
Publication date: 2021-03-09
Anticipated expiration: 2040-10-27
Also published as: CN112459851B

Abstract

The invention aims to provide a turbine movable blade cooling air supercharging device which comprises a turbine movable blade and a wheel disc, wherein the turbine movable blade is arranged on the wheel disc, each turbine movable blade is provided with a bleed air pipe, a flow guide disc is arranged outside the bleed air pipe, the bleed air pipes are fixed through the flow guide discs, the bleed air pipes are connected with air inlets of cold air channels on the front edge portions of the turbine movable blades, the bleed air pipes are inclined at an angle with the vertical center line in the circumferential direction, so that the direction of the air inlets on the lower portions of the bleed air pipes is consistent with the rotation direction of a rotor, and the air inlets are bevel air inlets in the same direction with the rotation direction. The invention realizes the control of the pressure of the cooling air entering different positions of the movable blade according to the requirement, reduces the requirement on the pressure of the cooling air and improves the utilization efficiency of the cooling air.

Description

Turbine movable blade cooling air supercharging device

Technical Field

The invention relates to a gas turbine, in particular to a cooling structure of the gas turbine.

Background

The 1 st stage movable blade of the turbine is the part with the highest working temperature in the gas turbine rotor, and works under the environment of high temperature and high stress for a long time, and the 1 st stage movable blade is the part with higher danger in the gas turbine, and generally, the 1 st stage movable blade is all hollow structure, causes that the solid part size of blade is little, and the wall thickness is thin, and structural strength is relatively poor, and the design safety can not improve, and is high to the requirement of processingquality. Once a stage of movable blade is out of order, the damage, the maintenance cost, the time and the difficulty of the movable blade at least on the through-flow part of the turbine are high, and therefore how to provide the reliability and the design safety margin of the stage 1 movable blade is a key technology for designing the combustion engine. As is known, when the temperature rises, the performance of the material is correspondingly reduced, and in order to enable the material to meet the strength requirement of the 1 st-stage movable blade, two ways are generally adopted, namely, using high-grade high-temperature alloy and supplying cooling air to the blade to reduce the temperature of the blade. The temperature resistance and strength of the high-temperature alloy are high in cost and high in difficulty, and cannot be realized in a short time, so that the research on the cooling technology of the blade is very important. The air inlet side of the blade is opposite to the air flow direction, and the dynamic pressure is highest, so that the cooling air pressure required by the air inlet side of the blade is highest, the pressure required by the middle part and the exhaust side of the blade is lower than that of the air inlet side, but in order to meet the requirement of cooling air of the air inlet side of the blade, the pressure loss is reduced, the pressure of the cooling air is ensured by means of selecting a high-pressure air extraction point and the like during redesign, the design difficulty is high, and the unit loss is large.

Disclosure of Invention

The invention aims to provide a turbine blade cooling air supercharging device which reduces the requirement on the cooling air pressure and improves the flow speed and the pressure of the cooling air.

The purpose of the invention is realized as follows:

the invention relates to a turbine rotor blade cooling air supercharging device, which is characterized in that: including turbine movable blade, rim plate, the turbine movable blade is installed on the rim plate, and each turbine movable blade all sets up a bleed pipe, and the outside of bleed pipe sets up the guiding disc, and it is fixed that the bleed pipe passes through the guiding disc, and the bleed pipe links to each other with the air inlet of the cold air runner of turbine movable blade leading edge part, and the bleed pipe is at a certain angle of circumference and perpendicular center line off-centre for bleed pipe lower part air inlet direction is unanimous with rotor direction of rotation, and the air inlet is the oblique air inlet the same with rotor direction of rotation.

The present invention may further comprise:

1. one part of cooling air is pressurized through the pumping action and then is supplied into a cavity at the front edge of the turbine movable blade through the air guide pipe, and the rest part of cooling air is introduced through an air flow channel formed by the flow guide disc and the wheel disc without the pressurization effect.

2. The bleed pipe is the reducing structure, and the diameter that is close to turbine movable vane direction is greater than the diameter of keeping away from turbine movable vane direction.

3. When the turbine rotor blade is in a static state, the air guide pipe is blocked by the small hole of the flow guide disc so as to prevent the air guide pipe from falling off, and when the turbine rotor blade is in an operating state, the air guide pipe is pressed against the air inlet of the cold air runner at the front edge part of the turbine rotor blade under the action of centrifugal force.

The invention has the advantages that: the invention realizes the control of the pressure of the cooling air entering different positions of the movable blade according to the requirement, reduces the requirement on the pressure of the cooling air and improves the utilization efficiency of the cooling air.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a view from direction a.

Detailed Description

The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:

with reference to fig. 1-2, a turbine bucket cooling air charging device includes a diaphragm 3 and a bleed air duct 4. The front parts of the turbine movable blades 1 and the wheel disc 2 are provided with air guide pipes for each blade, the air guide pipes are deviated from the vertical center line at a certain angle in the circumferential direction, the direction of an air inlet at the lower part of each air guide pipe 4 is consistent with the rotation direction of the rotor, and a beveled air inlet in the same rotation direction is processed at the air inlet. Because the air inlet side of the blade is opposite to the air flow direction and the dynamic pressure is highest, the cooling air pressure required by the air inlet side of the blade is highest, the air guide pipe 4 is connected with the air inlet of the cold air flow channel at the front edge part of the movable blade 1, so that the cold air pressurized by the air guide pipe 4 enters the front edge of the blade, and the cooling air in the rest inner cavities of the blade is introduced through the air flow channel formed by the flow guide plate 3 without the pressurization effect and the wheel disc 2. When the rotor rotates, the air guide pipe 4 is driven to rotate together, the oblique cutting air inlet of the air guide pipe 4 is the same as the rotation direction of the rotor, therefore, air is forcibly sucked into the air guide pipe 4 from the oblique cutting air inlet of the air guide pipe 4, the air guide pipe 4 plays a role similar to a centrifugal pump, due to the effect of centrifugal force, cold air is thrown out to be pressurized for the cold air, the air enters the inner cavity of the air inlet side of the 1 st-stage movable vane through the cold air inlet of the front edge of the vane after pressurization, the introduction of the pressurized cold air into the front edge is realized, and the non-pressurized cold air. At the outside guiding disk 3 of bleed pipe 4 for fixed bleed pipe 4, bleed pipe 4 adopts reducing structure, and the direction diameter that is close to the blade is big, and the direction diameter of keeping away from the blade is little, and during quiescent condition, bleed pipe 4 is blocked by 3 apertures of guiding disk, prevents to deviate from, and due to the effect of centrifugal force during the operation, bleed pipe 4 is thrown away, pushes up in the cooling air interface of blade. The structure increases the cold air flow, pressure and flow velocity of the stage 1 moving blade, increases the cooling heat exchange effect and reduces the requirement on the cooling air pressure.

Claims

1. A turbine moving blade cooling air supercharging device is characterized in that: including turbine movable blade, rim plate, the turbine movable blade is installed on the rim plate, and each turbine movable blade all sets up a bleed pipe, and the outside of bleed pipe sets up the guiding disc, and it is fixed that the bleed pipe passes through the guiding disc, and the bleed pipe links to each other with the air inlet of the cold air runner of turbine movable blade leading edge part, and the bleed pipe is at a certain angle of circumference and perpendicular center line off-centre for bleed pipe lower part air inlet direction is unanimous with rotor direction of rotation, and the air inlet is the oblique air inlet the same with rotor direction of rotation.

2. The turbine blade cooling air supercharging apparatus according to claim 1, wherein: one part of cooling air is pressurized through the pumping action and then is supplied into a cavity at the front edge of the turbine movable blade through the air guide pipe, and the rest part of cooling air is introduced through an air flow channel formed by the flow guide disc and the wheel disc without the pressurization effect.

3. The turbine blade cooling air supercharging apparatus according to claim 1 or 2, wherein: the bleed pipe is the reducing structure, and the diameter that is close to turbine movable vane direction is greater than the diameter of keeping away from turbine movable vane direction.

4. The turbine blade cooling air supercharging apparatus according to claim 1 or 2, wherein: when the turbine rotor blade is in a static state, the air guide pipe is blocked by the small hole of the flow guide disc so as to prevent the air guide pipe from falling off, and when the turbine rotor blade is in an operating state, the air guide pipe is pressed against the air inlet of the cold air runner at the front edge part of the turbine rotor blade under the action of centrifugal force.

5. The turbine blade cooling air supercharging apparatus according to claim 3, wherein: when the turbine rotor blade is in a static state, the air guide pipe is blocked by the small hole of the flow guide disc so as to prevent the air guide pipe from falling off, and when the turbine rotor blade is in an operating state, the air guide pipe is pressed against the air inlet of the cold air runner at the front edge part of the turbine rotor blade under the action of centrifugal force.