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US 9,869,250 B2Granted
Particle tolerant turboshaft engine
AssigneeUnited Technologies Corporation
InventorsPaul R. Hanrahan, Daniel Bernard Kupratis
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a core engine section which includes a compressor section and a core turbine section. The core engine is configured to rotate about a core axis. A drive turbine is configured to rotate about a drive turbine axis. A bypass passage connects an intake to the gas turbine engine directly with an exhaust of the drive turbine.
Claims20
A gas turbine engine comprising:
- a core engine section including a compressor section and a core turbine section, the core engine is configured to rotate about a core axis;
- a drive turbine configured to rotate about a drive turbine axis, wherein the drive turbine axis is separate from and extends in a direction generally transverse to the core axis;
- and
- a bypass passage connecting an intake to the gas turbine engine directly with an exhaust of the drive turbine.
1 more element
A method of operating a gas turbine engine comprising:
- directing a first portion of an inlet airflow through a bypass passage to a drive turbine exhaust;
- directing a second portion of an inlet airflow through a splitter downstream of a first compressor section of a core engine through a bypass duct to a drive turbine, wherein the drive turbine rotates about a drive turbine axis and the core engine rotates about a core axis, the drive turbine axis is generally transverse to the core axis;
- and
- directing a third portion of the inlet airflow through the core engine into the drive turbine.
1 more element
Dependencies are inferred from the claim text.