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US 10,378,454 B2Granted
Gas turbine engine with two-spool fan and variable vane turbine
AssigneeUnited Technologies Corporation
InventorDaniel Bernard Kupratis
Life of this patent
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Abstract
A method of operating a gas turbine engine includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.
Claims11
A method of operating a gas turbine engine comprising:
- modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust;
- modulating a variable area throat of a third stream bypass flow path to a third stream exhaust nozzle downstream of said first stage fan section, wherein said third stream bypass flow path is radially outboard of a second stream bypass flow path and a core flow path and said variable area throat includes a flow control door located downstream of an inlet to said third stream bypass flow path and said intermediate stage fan section is located downstream of said inlet to said third stream bypass flow path;
- and
- modulating variable low pressure turbine inlet guide vanes in response to an airspeed;
- modulating variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed;
- and
- modulating open said variable low pressure turbine inlet guide vanes in response to said airspeed being less than a desired airspeed;
- and
- modulating closed said variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed being less than said desired airspeed.
6 more elements
A method of operating a gas turbine engine comprising:
- modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust;
- modulating variable low pressure turbine inlet guide vanes in response to an airspeed;
- modulating variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed;
- modulating open said variable low pressure turbine inlet guide vanes in response to said airspeed being less than a desired airspeed;
- and
- modulating closed said variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed being less than said desired airspeed.
3 more elements
A method of operating a gas turbine engine comprising:
- modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust;
- modulating variable low pressure turbine inlet guide vanes in response to an airspeed;
- modulating variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed;
- modulating closed said variable low pressure turbine inlet guide vanes in response to said airspeed being greater than a desired airspeed;
- and
- modulating open said variable intermediate pressure turbine inlet guide vanes along said intermediate spool in response to said airspeed being greater than said desired airspeed.
3 more elements
Dependencies are inferred from the claim text.