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Cleaning system for a gas turbine engine

A technology for cleaning systems and gas turbines, which is applied in the field of cleaning systems and can solve problems such as unclean and effective cleaning

Inactive Publication Date: 2019-03-01
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, if the flow rate of the fluid injected into the gas turbine engine 800 is too low, the gas turbine engine 800 will not be cleaned and effectively washed

Method used

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  • Cleaning system for a gas turbine engine
  • Cleaning system for a gas turbine engine
  • Cleaning system for a gas turbine engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0013] figure 2 A schematic diagram of a cleaning system 100 according to one embodiment of the present disclosure is shown. Such as figure 2 As shown in , the cleaning system 100 can be used to clean a gas turbine engine 800 (such as figure 1 shown in ). Cleaning system 100 may include a fluid tank in which fluid is stored. In one embodiment, the fluid tank may include a cleaning water tank 1 storing cleaning water therein. For example, the volume of the cleaning water tank 1 may be larger than 120L.

[0014] The cleaning system 100 may include a nozzle arrangement 3 and a computer 5 . The cleaning tank 1 can be in fluid communication with the nozzle arrangement 3 via a connecting line 4 . The connecting line 4 may comprise a pump device 41 , which may be operatively coupled with the computer 5 . For example, the pump device 41 may include an electric motor 411 and a motor-driven pump 412 . The motor 411 can be operatively connected with the computer 5 to drive the ...

Embodiment 2

[0028] image 3 A schematic diagram of a cleaning system 200 for cleaning a gas turbine engine 800 according to another embodiment of the present disclosure is shown. Such as image 3 as shown in the figure 2 The cleaning system in 100 is different, image 3 The fluid tank of the cleaning system 200 in the above may further include a detergent tank 2 in which a detergent liquid is stored in addition to the cleaning water tank 1 . The detergent tank 2 can be coupled to a pump device 41 via a tank valve 11 . For example, the capacity of the detergent tank 2 may be greater than 40L.

[0029] see image 3 , in this embodiment, the cleaning system 200 may further include a selection valve 46 . The cleaning water tank 1 and the detergent tank 2 may be connected to the tank valve 11 via the selection valve 46, respectively. The selection valve 46 can be operatively coupled with the computer 5 , and the computer 5 can control the selection valve 46 to automatically switch betw...

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PUM

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Abstract

A cleaning system(100) for a gas turbine engine(800) is disclosed, which includes a fluid tank(l)with fluid therein, a nozzle device (3) for spraying the fluid from the fluid tank(l), a connection line (4) for connecting the fluid tank(l) with the nozzle device(3), and a computer(5). The connection line (4) includes a pump device (41) for pumping the fluid from the fluid tank (1) to the nozzle device (3), a flow meter (42) for measuring a flow rate of the fluid passing through the pump device (41), and a regulatory valve (43). The pump device (41), the flow meter (42) and the regulatory valve(43) are operably coupled with the computer (5), and the computer (5) controls the regulatory valve (43) to automatically regulate a flow rate of the fluid entering into the nozzle device (3) based ona measured flow rate of the fluid passing through the pump device and a fluid flow demand.

Description

Background technique [0001] The present disclosure relates generally to the field of aircraft engines, and more particularly to cleaning systems for gas turbine engines. [0002] Such as figure 1 As shown in , gas turbine engine 800 generally includes a compressor section R1 , a combustion section R2 , a turbine section R3 , and an exhaust section R4 in series flow order. In operation, air enters the inlet of compressor section R1 where one or more compressors progressively compress the air until it reaches combustion section R2. Fuel is mixed with the compressed air and combusted in combustion zone R2 to provide combustion gases. Combustion gases pass from combustion section R2 through a hot gas path defined within turbine section R3 and are then exhausted from turbine section R3 via exhaust section R4. The expanding combustion gases drive turbines within turbine section R3 and also generate thrust for propelling the aircraft. [0003] During operation of gas turbine engi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02B77/04F02C7/00F01D25/00
CPCF01D25/002B08B9/027G05D7/0635
Inventor 王鹏
Owner GENERAL ELECTRIC CO