CN210003341U

CN210003341U - Self-balancing cooling system of type turbine compressor

Info

Publication number: CN210003341U
Application number: CN201920991617.2U
Authority: CN
Inventors: 但光局; 侯春峰; 何晓燕; 龚由春; 李扬
Original assignee: Chongqing Jiangzeng Ship Heavy Industry Co Ltd
Current assignee: Chongqing Jiangzeng Ship Heavy Industry Co Ltd; Chongqing Jiangjin Shipbuilding Industry Co Ltd
Priority date: 2019-06-28
Filing date: 2019-06-28
Publication date: 2020-01-31
Anticipated expiration: 2029-06-28

Abstract

The utility model discloses an kind are through the turbine compressor's of cooling system balanced axial force self-balancing cooling system through the flow of control high pressure cryogenic cooling gas, can the counter shaft cooling, also can balance the axial force the cooling system includes the axle and the epaxial axle that sets gradually, low pressure end seal, low pressure section cooling space, low pressure end pressure balance chamber, low pressure side thrust forming face, low pressure end mechanical seal, sound leaf district, high pressure side thrust forming face, high pressure end pressure balance chamber, high pressure end mechanical seal, high pressure section cooling space, high pressure end seal, set up the cooling gas import between high pressure end mechanical seal, the high pressure section cooling space for connect the cooling gas source, set up the cooling gas export between high pressure section cooling space, the high pressure end seal, the low pressure end pressure balance chamber is connected through the structure passageway to the cooling gas export, set up the cooling gas exhaust port between low pressure end seal, the low pressure section cooling space for discharge the cooling gas.

Description

Self-balancing cooling system of type turbine compressor

Technical Field

The invention relates to the field of high-temperature and high-pressure turbines and high-temperature and high-pressure compressors, in particular to a self-balancing cooling system of turbine compressors.

Background

In order to improve the overall efficiency of the turbine unit and the compressor unit, more and more new working media are used in the turbine unit and the compressor, such as supercritical CO2, ultra-supercritical CO2, helium and the like, which generally have the characteristics of high pressure and high temperature, so that the turbine unit and the compressor unit shaft bear great axial force and ultrahigh temperature.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides self-balancing cooling systems and methods of a turbine compressor for balancing axial force through the cooling systems.

The purpose of the invention is realized as follows:

self-balancing cooling system of turbine compressor, which comprises a shaft and a low pressure end seal, a low pressure section cooling area, a low pressure end mechanical seal, a moving and static blade area, a high pressure end mechanical seal, a high pressure section cooling area, a high pressure end seal which are arranged on the shaft in sequence, wherein the shaft is provided with a section large diameter section with increased diameter, the low pressure end mechanical seal and the moving and static blade area are arranged on the large diameter section, the low pressure end shaft shoulder of the large diameter section is a low pressure side pressure forming surface, the high pressure end shaft shoulder of the large diameter section is a high pressure side thrust forming surface, the areas of the low pressure side pressure forming surface and the high pressure side thrust forming surface are equal, a low pressure end pressure balancing cavity is arranged between the low pressure section cooling area and the low pressure side pressure forming surface, a high pressure end pressure balancing cavity is arranged between the high pressure side thrust forming surface and the high pressure end mechanical seal, and the high pressure balancing cavity is communicated with the inner cavity of the moving and static blade area, so that the pressure in the high pressure balancing cavity is equal to;

set up the cooling gas import between high pressure end mechanical seal, the high-pressure section cooling district for connect the cooling air supply, set up the cooling gas export between high pressure section cooling district, the high-pressure end is sealed, the cooling gas export passes through structural channel and connects low pressure end pressure balance chamber, set up the cooling gas exhaust port between the low pressure end is sealed, the low pressure section cooling district for discharge cooling gas.

self-balancing cooling method for turbine compressor comprises self-balancing cooling system, cooling gas inlet connected with cooling gas source, and pressure of the cooling gas source equal to working medium pressure in pressure balancing cavity at high pressure end;

the cooling gas is firstly introduced to the outer side of the high-pressure end mechanical seal from a cooling gas source, so that working medium gas in the high-pressure end pressure balance cavity is prevented from leaking outwards, and meanwhile, the cooling gas enters a cooling channel between a high-pressure section cooling area and the shaft to cool the high-pressure section of the shaft;

then, introducing the cooling gas into a low-pressure end pressure balance cavity through a structural channel, cooling the shaft by the cooling gas in the low-pressure end pressure balance cavity entering a cooling channel between a low-pressure section cooling area and the shaft, and then discharging the cooling gas out of a cooling system;

in the cooling process, the pressure of the cooling gas in the low-pressure end pressure balance cavity is equal to the pressure of the working medium gas in the high-pressure end pressure balance cavity, and the areas of the low-pressure side pressure forming surface and the high-pressure side thrust forming surface are equal, so that the axial forces on the low-pressure side thrust forming surface and the high-pressure side thrust forming surface are equal in magnitude and opposite in direction and are mutually offset, and the axial forces are balanced while the shaft is cooled.

By adopting the technical scheme, the axial thrust bearing device can meet the cooling requirement of the high-temperature high-pressure turbine unit on the shaft, and can also effectively balance the axial force of the high-temperature high-pressure turbine unit and the high-temperature high-pressure compressor unit, thereby reducing the requirement of the units on the axial thrust bearing. The control method of the cooling gas can be designed according to the requirements of the shaft to the cooling system. Since the existing turbine unit and compressor unit are arranged in the same manner, the application can adapt to both the compressor and the turbine.

Drawings

Fig. 1 is a schematic structural view of the present invention (upper half).

Reference numerals

In the drawings, 1-axis; 2-sealing the low-pressure end; 3-a low-pressure section cooling zone; 4-a low pressure end pressure balance chamber; 5-low pressure side thrust forming surface; 6-mechanical sealing of the low-pressure end; 7-a moving and static leaf area; 8-high pressure side thrust forming surface; 9-high pressure end pressure balance cavity; 10-mechanical sealing of the high-pressure end; 11-a high pressure section cooling zone; 12-high pressure end seal.

Detailed Description

As shown in FIG. 1, self-balancing cooling systems for turbo compressors comprise a shaft 1, a low pressure end seal 2, a low pressure section cooling area 3, a low pressure end pressure balancing cavity 4, a low pressure side pressure forming surface 5, a low pressure end mechanical seal 6, a moving stationary blade area 7, a high pressure side thrust forming surface 8, a high pressure end pressure balancing cavity 9, a high pressure end mechanical seal 10, a high pressure section cooling area 11, and a high pressure end seal 12. the low pressure end pressure balancing cavity 4 is a section cavity between the low pressure section cooling area 3 and the low pressure end mechanical seal, and the low pressure end pressure balancing cavity 4 and the high pressure end pressure balancing cavity 9 are connected through a structural channel.

The shaft 1 is provided with sections of large diameter sections with increased diameters, the low-pressure end mechanical seal 6 and the movable stationary blade area 7 are arranged on the large diameter sections, the low-pressure end shaft shoulder of the large diameter section is a low-pressure side pressure forming surface 5, the high-pressure end shaft shoulder of the large diameter section is a high-pressure side thrust forming surface 8, the areas of the low-pressure side pressure forming surface 5 and the high-pressure side thrust forming surface 8 are equal, the high-pressure end pressure balance cavity 9 is communicated with the inner cavity of the movable stationary blade area 7, and the pressure in the high-pressure end pressure balance cavity 9 is equal to the pressure in the movable stationary blade area 7.

Set up the cooling gas import between high-pressure side mechanical seal 10, the high-pressure section cooling district 11 for connect the cooling air supply, set up the cooling gas export between high-pressure section cooling district 11, the high-pressure side seal 12, the cooling gas export passes through structural passage and connects low pressure end pressure balance chamber 4, set up the cooling gas exhaust port between low pressure side seal 2, the low pressure section cooling district 3, be used for discharging the cooling gas.

The turbine compressor is provided with a shell, the structural channel can be arranged in the shell, and pipelines can also be adopted.

self-balancing cooling method for turbine compressor:

the high-pressure low-temperature cooling gas is firstly introduced into the high-pressure end mechanical seal 10 from the high-pressure low-temperature cooling gas source to prevent high-temperature high-pressure working medium gas inside from leaking outwards, meanwhile, the cooling gas enters a cooling channel between the high-pressure section cooling area 11 and the shaft 1 to cool the shaft, then the cooling gas is introduced into the low-pressure end pressure balance cavity 4 through a structural channel, part of the cooling gas in the low-pressure end pressure balance cavity 4 enters the cooling channel between the low-pressure section cooling area 3 and the shaft 1 to cool the shaft, and then the cooling gas is discharged out of the cooling system in a proper mode.

The present invention has been described in terms of specific examples, which are provided to aid understanding of the invention and are not intended to be limiting. Numerous derivations, modifications, or substitutions may be made by those skilled in the art to which the invention pertains.

Claims

The self-balancing cooling system of the turbo compressor is characterized by comprising a shaft (1), and a low-pressure end seal (2), a low-pressure section cooling area (3), a low-pressure end mechanical seal (6), a moving and static blade area (7), a high-pressure end mechanical seal (10), a high-pressure section cooling area (11) and a high-pressure end seal (12) which are sequentially arranged on the shaft (1), wherein a section diameter-increased large-diameter section is arranged on the shaft (1), the low-pressure end mechanical seal (6) and the moving and static blade area (7) are arranged on the large-diameter section, a low-pressure side pressure forming surface (5) is arranged on a low-pressure end shaft shoulder of the large-diameter section, a high-pressure side thrust forming surface (8) is arranged on a high-pressure side shaft shoulder of the large-diameter section, the areas of the low-pressure side thrust forming surface (5) and the high-pressure side thrust forming surface (8) are equal, a low-pressure end pressure balancing cavity (4) is arranged between the low-pressure section cooling area (3) and the low-pressure side pressure forming surface (5), the high-pressure side thrust forming surface (8) and the high-pressure balancing cavity (9) is communicated with the pressure balancing cavity (9) of the high-pressure end inner cavity (7);

set up the cooling gas import between high-pressure side mechanical seal (10), high-pressure section cooling district (11) for connect the cooling gas source, set up the cooling gas export between high-pressure section cooling district (11), the high-pressure side seal (12), the cooling gas export passes through structural channel and connects low pressure end pressure balance chamber (4), set up the cooling gas exhaust port between low pressure side seal (2), the low-pressure section cooling district (3) for discharge cooling gas.