Multistage gas turbine engine with differential drive of compressor
AssigneeRaytheon Technologies Corporation
InventorsDaniel Bernard Kupratis, Mark Tu, Paul R Hanrahan, Arthur M. Salve, Jr.
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Abstract
A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; a high pressure compressor connected to a high pressure compressor spool; and a differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear connected to the high pressure compressor spool.
Claims20
A gas turbine engine, comprising:
- a turbine having a first stage and a second stage, the first stage connected to a first stage spool and the second stage connected to a second stage spool;
- a high pressure compressor connected to a high pressure compressor spool;
- and
- a differential system having a first stage input gear connected to the first stage spool, a second stage input gear connected to the second stage spool and an output gear connected to the high pressure compressor spool.
A gas turbine engine, comprising:
- a turbine having a first stage and a second stage, the first stage connected to a first stage spool and the second stage connected to a second stage spool;
- a high pressure compressor connected to a high pressure compressor spool;
- and
- a differential system having a first stage input gear connected to the first stage spool, a second stage input gear connected to the second stage spool, a first stage output gear connected to the high pressure compressor spool and a second stage output gear connected to the high pressure compressor spool.
A method for distributing power from a turbine section of a gas turbine engine, comprising:
- generating a first stage rotational power from a first stage of the turbine section;
- generating a second stage rotational power from a second stage of the turbine section;
- inputting into a differential system the first stage rotational power via a first stage spool and the second stage rotational power via a second stage spool;
- and
- outputting from the differential system a compressor stage rotational power configured to drive a high pressure compressor section of the gas turbine engine.
Dependencies are inferred from the claim text.