Unlock instant, AI-driven research and patent intelligence for your innovation.

Internal cooling structure of gas turbine 2-stage turbine rotor

A gas turbine and internal cooling technology, which is applied to mechanical equipment, engine components, machines/engines, etc., can solve the problems of no internal cooling structure, etc., and achieve the effect of improving efficiency and reducing consumption

Active Publication Date: 2019-01-04
HARBIN ELECTRIC CO LTD
View PDF4 Cites 9 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that there is no suitable internal cooling structure for the existing two-stage gas turbine rotor structure with different speeds, and to provide an internal cooling structure for the two-stage turbine rotor of the gas turbine

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Internal cooling structure of gas turbine 2-stage turbine rotor

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0023] Specific implementation mode one: combine figure 1 Describe this embodiment, the internal cooling structure of a gas turbine two-stage turbine rotor in this embodiment, including a cooling air guide device 1, a first-stage turbine disk 5, a second-stage turbine disk 12, and a turbine front end Shaft 29 and turbine rear end shaft 20, described turbine front end shaft 29 is a hollow shaft, turbine rear end shaft 20 is arranged in the turbine front end shaft 29, and turbine front end shaft 29 is the same as turbine rear end shaft 20 Arranged at the center of the shaft, the turbine front end shaft 29 is provided with a first-stage turbine disc connection ring 38 in the circumferential direction, and the turbine rear end shaft 20 is provided with a second-stage turbine disc connection ring 39 in the circumferential direction. The first-stage turbine disk 5 is fixedly installed on the first-stage turbine disk connection ring 38, and the second-stage turbine disk 12 is fixedly...

specific Embodiment approach 2

[0028] Specific implementation mode two: combination figure 1 Describe this embodiment, the internal cooling structure of a second-stage turbine rotor of a gas turbine in this embodiment, the upper end of the cooling air guiding device 1 adopts the grate tooth sealing structure 3 and the top end of the first-stage turbine disc 5 Coordinated installation, the middle part of the cooling air guide device 1 and the middle part of the first-stage turbine disc 5 are installed in cooperation with the first comb-tooth sealing structure 35, and the top of the cooling air guide device 1 and the top of the first-stage turbine disc 5 The bottom chamber 36 of the blade is formed; the lower part of the cooling air guiding device 1 is connected to the housing, and the housing is equipped with an air seal 33, and the air seal 33 is installed in cooperation with the turbine front end shaft 29 by the second comb-tooth sealing structure 32, cooling The air guiding device 1, the housing 41, the f...

specific Embodiment approach 3

[0029] Specific implementation mode three: combination figure 1 Describe this embodiment, the internal cooling structure of a second-stage turbine rotor of a gas turbine in this embodiment, the lower end of the partition member 8 installed on the inner ring 7 of the stator blade adopts the third comb-tooth sealing structure 19 and the first The lower end of the stage turbine disc 5 is installed in cooperation.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to an internal cooling structure of a gas turbine 2-stage turbine rotor, belonging to the gas turbine structure field. In order to solve the problem that for the existing two-stage turbine gas turbine rotor structure with different shafts and different rotational speeds, there is no suitable internal cooling structure. The invention comprises a cooling air guide device, a first stage turbine disk, a second stage turbine disk, a turbine front shaft and a turbine rear shaft, the turbine front shaft is a hollow shaft, the turbine rear shaft is disposed in the turbine front shaft, the turbine front shaft and the turbine rear shaft are arranged coaxially, the turbine front shaft is circumferentially provided with a first turbine disk connecting ring, the turbine rear shaftis circumferentially provided with a second turbine disk connecting ring, the first stage turbine disk is fixedly mounted on the first turbine disk connecting ring, and the second stage turbine diskis fixedly mounted on the second turbine disk connecting ring. The invention maximizes the consumption of the high-pressure cooling air, improves the efficiency of the gas turbine, and realizes the internal cooling system of the turbine rotor with different shafts and different rotational speeds.

Description

technical field [0001] The invention relates to an internal cooling system of a gas turbine, belonging to the field of gas turbine structures. Background technique [0002] At present, for the gas turbine unit, an effective way to improve its cycle efficiency is to increase the gas inlet temperature of the gas turbine, and an effective way to increase the initial temperature is to cool and protect the high-temperature components of the gas turbine through a reasonable cooling air system design. Due to the limited temperature that the high-temperature materials used in the current turbine blades can withstand, reliable cooling measures must be taken to reduce the operating temperature of the high-temperature components of the gas turbine, especially the turbine blades, so as to ensure the safe operation of the gas turbine and improve The cooling effect of turbine working blades is an inevitable requirement for the development of high-efficiency gas turbines. [0003] For gas...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/08F01D11/00F01D11/02
CPCF01D5/08F01D11/001F01D11/02
Inventor 葛春醒冯永志姜东坡赵俊明王颖孙涛王政先张秋鸿
Owner HARBIN ELECTRIC CO LTD