Gas turbine offline compressor wash with buffer air from combustor

Patent metadata

Field	Value
Publication number	US-9631512-B2
Application number	US-201313756342-A
Country	US
Kind code	B2
Filing date	Jan 31, 2013
Priority date	Jan 31, 2013
Publication date	Apr 25, 2017
Grant date	Apr 25, 2017

Abstract

A system and method for washing a gas turbine engine. The method for washing the gas turbine engine includes coupling a pressurized air supply assembly to an air supply and to a secondary air system, cranking a compressor rotor assembly of the gas turbine engine, supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly, and spraying a cleaner into the compressor.

First claim

What is claimed is:

1. A method for washing a compressor in a gas turbine engine, the method comprising:
removing an injector from an injector port of the gas turbine engine;
installing a local air supply adapter to the injector port, the local air supply adapter being part of a pressurized air supply assembly, the gas turbine engine being an air supply;
coupling the pressurized air supply assembly to a secondary air system of the gas turbine engine including coupling the pressurized air supply assembly to a buffer air path, the buffer air path leading to a first seal of at least one intermediate bearing assembly of the gas turbine engine;
cranking a compressor rotor assembly of the gas turbine engine;
supplying offline buffer air to the secondary air system from the air supply and via the pressurized air supply assembly; and
delivering cleaner to the compressor.

2. The method of claim 1 , wherein the supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly includes keeping a combustor case bleed at least partially closed during the delivering cleaner to the compressor.

3. The method of claim 1 , wherein the coupling the pressurized air supply assembly to the secondary air system of the gas turbine engine further includes
coupling the pressurized air supply assembly to a cooling air path, the cooling air path leading to one or more cooling passages of at least one turbine rotor assembly of the gas turbine engine.

4. The method of claim 3 , further comprising
accessing a compressor port, including decoupling secondary air plumbing pneumatically coupled to the compressor port;
installing a secondary air cap, including capping off the compressor port;
accessing the buffer air path, including decoupling secondary air plumbing outside a combustor at a mating buffer air path mounting flange;
accessing the cooling air path, including decoupling secondary air plumbing outside a combustor at a mating cooling air path mounting flange;
wherein the coupling the pressurized air supply assembly to the buffer air path includes coupling the pressurized air supply assembly to the mating buffer air path mounting flange; and
wherein the coupling the pressurized air supply assembly to the cooling air path includes coupling the pressurized air supply assembly to the mating cooling air path mounting flange.

5. The method of claim 4 , wherein the secondary air cap includes a bleed vent, the method further comprising:
rinsing the cleaner from the compressor; and
purging the secondary air cap by opening the bleed vent after the rinsing the cleaner from the compressor.

6. The method of claim 1 , wherein the coupling the pressurized air supply assembly to the secondary air system of the gas turbine engine includes coupling the pressurized air supply assembly to a buffer air path, the buffer air path leading one or more buffered seals of at least one end bearing assembly and at least one intermediate bearing assembly of the gas turbine engine.

7. The method of claim 6 , further comprising coupling an air supply pneumatic couple to a shop air supply, the shop air supply being other than the gas turbine engine; and
wherein the supplying offline buffer air to the secondary air system includes supplying offline buffer air to the one or more buffered seals of at least one end bearing assembly from the shop air supply via the air supply pneumatic couple.

8. The method of claim 1 , wherein the cranking the compressor rotor assembly includes operating a starter of the gas turbine engine without fuel supplied, and further includes cranking the compressor to at least 20 percent of a normal operating speed of the compressor.

9. The method of claim 1 , wherein the cranking the compressor rotor assembly includes cranking the compressor such that a maximum output pressure of the compressor is at least 0.5 psig, as gauged off atmospheric pressure.

10. The method of claim 1 , wherein the local air supply adapter includes an air supply extension;
wherein the installing the local air supply adapter to the injector port includes extending the air supply extension to or into a combustion chamber; and
wherein the supplying offline buffer air to the secondary air system includes supplying offline buffer air from the combustion chamber.

11. The method of claim 1 , wherein the injector port is in the upper half of a combustor of the gas turbine engine.

12. A method for washing a gas turbine engine, the gas turbine engine including a compressor, a combustor, and a turbine, the method comprising:
removing an injector from an injector port;
installing a local air supply adapter to the injector port;
cranking the compressor of the gas turbine engine;
supplying compressed air to a cooling air path of the gas turbine engine via the secondary air system;
supplying compressed air to a buffered seal of an intermediate bearing assembly of the gas turbine engine via the secondary air system;
distributing a cleaner into the compressor; and
supplying compressed air to a secondary air system of the gas turbine engine from the local air supply adapter.

13. The method of claim 12 , further comprising:
coupling an air supply pneumatic couple to a shop air supply, the shop air supply being other than the gas turbine engine;
supplying compressed air to a mixed air path of the gas turbine engine via the secondary air system; and
wherein the compressed air is supplied from both the local air supply adapter and the air supply pneumatic couple.

14. The method of claim 12 , wherein the cranking the compressor of the gas turbine engine includes operating a starter of the gas turbine engine such that the compressor is rotated to at least 20 percent of a normal operating speed of the compressor, and such that a maximum output pressure of the compressor is at least 0.5 psig, as gauged off atmospheric pressure.

15. The method of claim 12 , further comprising:
accessing a compressor port, including decoupling secondary air plumbing pneumatically coupled to the compressor port;
installing a secondary air cap, including capping off the compressor port, the secondary air cap including a bleed vent;
rinsing the cleaner from the compressor; and

purging the secondary air cap by opening the bleed vent after the rinsing the cleaner from the compressor.

Assignees

• Solar Turbines Inc

Inventors

• Lockyer John Frederick

Classifications

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F01D25/002 Primary

  Cleaning of turbomachines · CPC title