RU1802173C - Gas turbine wheel - Google Patents

Abstract

Usage: in turbomachinery, mainly cooled gas turbines. The inventive cooling air under pressure of a high-pressure head through a hollow front shaft 21 and end and radial grooves 12 and 14 enters the cavity 4, formed by the deflector 4 and the side surface of the disk 1, and cools the disk 1. Under the action of centrifugal forces, the air through the channels 9, the chamber 16 and the tube 11 enters the front channel 7 of the hollow blade 6, then flowing through the back channel 8, the air cools the blade 6 and through the tube 11, the chamber 17 and the channel 10 enters the cavity 5. The leaking air cools the rear surface of the disk 1, then through PS 15 and 13 enters the rear of the shaft cavity 22 and is discharged outside. 1 ill.

Description

FIELD OF THE INVENTION This invention relates to a turbomachinery, mainly to impellers of cooled gas turbines.

The aim of the invention is to increase reliability and efficiency.

The drawing shows the meridional section of the impeller.

The impeller contains a disk 1 with deflectors 2 and 3, forming cavities 4 and 5 with its lateral surfaces, mounted on the disk 1 of the blade 6, each of which has front and rear channels 7 and 8, respectively, and communicated with the latter and the cavity mi 4 and 5, channels 9 and 10 of the inlet and outlet of the cooling medium. Each blade 6 in the area of the lock is equipped with adapters in the form of tubes 11 mounted on its end surfaces and connected to the front and rear channels 7 and 8. In the hub part of the disk. end grooves 12 and 13 are made, and in the hub part of deflectors 2 and 3 there are made radial grooves 14 and 15 communicated with cavities 4 and 5. Channels 9. and 10 are made in the peripheral part of deflectors 2 and 3, forming with end surfaces of the lock chambers 1 6 and 17 connected to channels 9 and 10, and tubes

11 are located in the chambers 16 and 17 and are sealed relative to the deflectors 2 and 3 with seals 18 and 19. Radial ribs 20 are made on the deflector 2. The disk 1 is connected to the front and rear hollow shafts 21 and 22 ...

The impeller of a gas turbine operates as follows.

Cooling air from a fan, air hub or under pressure of a pressure head through a hollow front shaft 21 and grooves

12 and 14 enters the cavity 4 and the leak cools the disk 1. Under the action of centrifugal forces, air passes through the channels 9 of the chamber 16 and the tube 11 into the internal cavity of the blade 6 into the front channel 7. The air inside the blade 6 leaks heat

from the walls of the blade b and through the tubes 11, the chamber 17 and the channel 10 for the removal of the cooling medium enters the cavity 5. The leaked air cools the rear surface of the disk 1, then through the grooves 15 and 13 it enters

the internal cavity of the rear shaft 22 and is brought out. When the blades are cooled by low pressure air, heat transfer is intensified due to an increase in the temperature head between the cooled surfaces and the air.

Claims (1)

SUMMARY OF THE INVENTION A gas turbine impeller comprising a disk with deflectors forming with its lateral surfaces, cavities mounted on the blade of the blade, each of which has front and rear channels, and channels for supplying and discharging a cooling medium communicated with the latter and the cavities, characterized in that, in order to increase reliability and efficiency, each blade in the lock zone is equipped with adapters in the form of tubes mounted on its end surfaces and connected to the front and rear channels, end and radial grooves are made in the hub part of the disk and deflectors, respectively communicated with the cavities, and the channel s supply and discharge of the cooling medium formed in the peripheral part of baffles forming with the end surfaces of the lock chamber connected to the medium supply and removal channels, and a tube arranged in the chamber and sealed relative to the baffles.