System and method of transferring power in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10563593-B2
Application number	US-201614987271-A
Country	US
Kind code	B2
Filing date	Jan 4, 2016
Priority date	Jan 4, 2016
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

A method of extracting work from a convertible gas turbine engine having a core flowpath and a bypass flowpath. The method comprises operating the convertible gas turbine engine at a first volumetric flow rate through the core flowpath and a second volumetric flow rate through the bypass flowpath to produce a first work output of the convertible gas turbine engine; extracting the first work output via an unshrouded fan and a shaft at a first fan to shaft extraction ratio; altering the second volumetric flowrate through the bypass flowpath while maintaining the first work output; and extracting the first work output via an unshrouded fan and a shaft at a second fan to shaft extraction ratio.

First claim

What is claimed is:

1. A method of rapidly transitioning between turboshaft and turbofan operations in a convertible gas turbine engine comprising an unshrouded inlet fan, a plurality of variable inlet guide vanes axially aligned with and anchored to a set of fixed inlet guide vanes and a shaft, a method comprising:
establishing airflow through the set of fixed inlet guide vanes to an engine core flowpath to achieve maximum operating efficiency of said convertible gas turbine engine; and
transferring power between said unshrouded inlet fan and said shaft while maintaining a constant power output of said convertible gas turbine engine by altering the alignment of the plurality of variable inlet guide vanes forward of a bypass flowpath.

2. The method of claim 1 wherein power is transferred from said unshrouded inlet fan to said shaft by altering the alignment of said plurality of variable inlet guide vanes to decrease airflow through the bypass flowpath.

3. The method of claim 1 wherein power is transferred from said shaft to said unshrouded inlet fan by altering the alignment of said plurality of variable inlet guide vanes to increase airflow through the bypass flowpath.

4. The method of claim 1 wherein said alignment of said plurality of variable inlet guide vanes is controlled by a controller via an actuator.

5. The method of claim 4 wherein said alignment of said plurality of variable inlet guide vanes is adjusted based on a predetermined schedule of alignments.

6. The method of claim 5 wherein said predetermined schedule of alignments includes a plurality of alignments for said plurality of variable inlet guide vanes to transfer loading of the convertible gas turbine engine between turboshaft and turbofan operations while maintaining steady overall loading of the convertible gas turbine engine.

7. The method of claim 1 wherein said convertible gas turbine engine is affixed to an aircraft and said turbofan operations provide propulsive force to said aircraft.

8. The method of claim 1 wherein said shaft is selectably coupled to a power transfer shaft via a clutch.

9. The method of claim 1 wherein said shaft is coupled to a power transfer shaft.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Mcneil Charles L
• Kusnierek John

Classifications

• F02C9/20 Primary

  by throttling; by adjusting vanes · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title

• F02C3/113

  with variable power transmission between rotors · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title