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US 2015/0176484 A1Published application
Geared turbofan with a gearbox aft of a fan drive turbine
AssigneeUnited Technologies Corporation
InventorsFrederick M. SCHWARZ, Gabriel L. SUCIU
Life of this patent
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Abstract
A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan.
Claims26
A gas turbine engine comprising:
- a drive turbine configured to drive a fan section;
- and
- a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan, an output of the speed change mechanism connected to the fan, wherein the drive turbine is a fixed stator turbine and the fixed stator is located axially between a pair of turbine stages.
(canceled)
A method of operating a gas turbine engine comprising:
- rotating a fan drive turbine at a first rotational speed, wherein the fan drive turbine is a fixed stator turbine and the fixed stator is located axially between a pair of turbine stages;
- reducing the first rotational speed to a second rotational speed using a speed change mechanism positioned axially downstream of the fan drive turbine;
- and
- rotating a fan positioned upstream of the fan drive turbine and the speed change mechanism at the second rotational speed.
1 more element
(canceled)
A gas turbine engine comprising:
- a drive turbine configured to drive a fan section;
- and
- a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan, an output of the speed change mechanism connected to the fan wherein the speed change mechanism is a star gear system.
Dependencies are inferred from the claim text.