Back to results
US 9,850,821 B2Granted
Gas turbine engine with fan-tied inducer section
AssigneeUnited Technologies Corporation
InventorsDaniel Bernard Kupratis, Frederick M. Schwarz
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.
Claims26
A gas turbine engine comprising:
- a shaft defining an axis of rotation;
- an epicyclic gear train driven by the first shaft;
- a fan including a fan rotor driven by the epicyclic gear train;
- a compressor section comprising a plurality of compressor stages driven by the shaft;
- and
- at least one inducer stage positioned aft of the fan and coupled for rotation with the fan rotor, and wherein the at least one inducer stage is positioned upstream of the compressor section.
3 more elements
A gas turbine engine comprising:
- a first shaft defining an axis of rotation;
- an epicyclic gear train driven by the first shaft;
- a fan section including at least one fan blade coupled to a fan rotor wherein the fan rotor is driven by the epicyclic gear train;
- a compressor section comprising at least a low pressure compressor driven by the first shaft and a high pressure compressor driven by a second shaft;
- a turbine section comprising at least a low pressure turbine configured to drive the first shaft and a high pressure turbine configured to drive the second shaft;
- and
- at least one inducer stage positioned aft of the fan blade and coupled for rotation with the fan rotor about the axis of rotation, and wherein the at least one inducer stage is positioned forward of the compressor section.
4 more elements
Dependencies are inferred from the claim text.