Compressor wash with air to turbine cooling passages
AssigneeSolar Turbines Incorporated
InventorJohn Frederick Lockyer
Life of this patent
Estimating the term…
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.
Claims19
A method for washing a compressor in a gas turbine engine, the method comprising:
- coupling a pressurized air supply assembly to an air supply;
- 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;
- coupling the pressurized air supply assembly to a buffer air path, the buffer air path leading to one or more buffered seals of at least one bearing assembly of the gas turbine engine;
- 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
- delivering cleaner to the compressor.
(canceled)
A method for washing a gas turbine engine, the gas turbine engine including a compressor, a combustor, and a turbine, the method comprising:
- shutting off fuel to the combustor;
- 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;
- cranking the compressor of the gas turbine engine;
- distributing a cleaner into the compressor;
- supplying compressed air to a cooling air path of the gas turbine engine via a secondary air system;
- 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.
16-20. (canceled)
A method for washing a compressor in a gas turbine engine, the method comprising:
- coupling a pressurized air supply assembly to an air supply;
- removing an injector from an injector port;
- installing a local air supply adapter to the injector port;
- 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;
- cranking a compressor rotor assembly of the gas turbine engine;
- delivering cleaner to the compressor;
- and
- supplying pressurized offline buffer air from the air supply to the pressurized air supply assembly including keeping a combustor case bleed at least partially closed during the delivering cleaner to the compressor.
Dependencies are inferred from the claim text.