Gas turbine engine with axial flow fan with twin stream impeller and variable area bypass nozzle

Patent metadata

Field	Value
Publication number	US-9926883-B1
Application number	US-201715597216-A
Country	US
Kind code	B1
Filing date	May 17, 2017
Priority date	Feb 11, 2017
Publication date	Mar 27, 2018
Grant date	Mar 27, 2018

Abstract

A gas turbine engine for a small aircraft such as a UAV having a bypass flow with a variable area bypass nozzle located at an outlet of the bypass channel, the nozzle having one position with a maximum flow area and a second position with a minimal flow area. The compressor is a twin stream compressor with an inner flow path for compressed air to the combustor and an outer flow path for the bypass channel. A fan stage can be used in front of the compressor.

First claim

I claim the following:

1. A single spool gas turbine engine comprising:
a twin stream centrifugal compressor with an inner core flow path and an outer bypass flow path, the outer bypass flow path of the twin stream centrifugal compressor includes a row of fan blades to compress a bypass flow through a bypass flow channel;
a combustor to receive compressed air from the inner flow path of the twin stream centrifugal compressor;
a turbine driving the twin stream centrifugal compressor;
an outlet at an end of the bypass flow channel; and,
a two-position variable area bypass nozzle at the outlet of the bypass flow channel to change a flow area of the outlet of the bypass flow channel of the single spool gas turbine engine, the two-position variable area bypass nozzle is a sliding valve connected to an actuator for movement to a minimal flow area position and a spring for movement to a fully open position.

2. The gas turbine engine of claim 1 , and further comprising:
the single spool gas turbine engine includes a fan stage connected to the twin stream centrifugal compressor upstream from the twin stream centrifugal compressor.

3. The gas turbine engine of claim 1 , and further comprising:
the actuator for the sliding valve is a hydraulic actuator with a fuel used for the gas turbine engine as the hydraulic fluid for the hydraulic actuator.

Assignees

• Florida Turbine Tech Inc

Inventors

• Ress Robert A

Classifications

• F01D17/141

  by means of shiftable members or valves obturating part of the flow path · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K3/02

  in which part of the working fluid by-passes the turbine and combustion chamber · CPC title

• F02K3/06

  with front fan · CPC title

• F02C3/04

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