Free stream intake with particle separator for reverse core engine

Patent metadata

Field	Value
Publication number	US-9644537-B2
Application number	US-201314142968-A
Country	US
Kind code	B2
Filing date	Dec 30, 2013
Priority date	Mar 14, 2013
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

A gas turbine engine has a fairing and an air intake that includes an air inlet embedded within the fairing for supplying free stream atmospheric air to a gas generator.

First claim

What is claimed is:

1. A gas turbine engine freestream intake, comprising:
a wing-shaped fairing having a leading edge, a trailing edge, an inner edge, an upper surface, a lower surface, and an outer edge surface extending from the leading edge to the trailing edge;
an air intake connected to an air inlet embedded within the wing-shaped fairing, said air intake located in said leading edge and supplying free stream atmospheric air to a gas generator within a gas turbine engine;
a curved duct connected to said air inlet, said curved duct turning the free stream atmospheric air towards said inner edge;
a particle separation outlet connected to an outer curved portion of said curved duct;
a channel particle outlet located in said trailing edge; and
a channel connecting said particle separation outlet to said channel particle outlet, wherein solid particles in said free stream atmospheric air follow a substantially straight path from said air intake through said outer curved portion to said particle separation outlet and then through said channel to said channel particle outlet.

2. The gas turbine engine freestream intake of claim 1 , including an exterior wall surround at least a portion of an engine core, said inner edge is blended into said exterior wall surrounding at least the portion of said engine core.

3. An aircraft comprising the gas turbine engine freestream intake of claim 1 .

4. An aircraft comprising:
a fuselage;
a propulsion system comprising
a pair of gas generators located at a tail section of said fuselage, each one of said pair of gas generators comprising a reverse engine core;
a propulsor section with a pair of free turbines and a pair of fans, each one of said pair of free turbines driving a respective one of said pair of fans; each one of said pair of free turbines being driven by a fluid generated by a respective one of said pair of gas generators;

a pair of wing-shaped fairings mounted to said tail section of said fuselage, each one of said pair of wing-shaped fairings defined by a leading edge, a trailing edge, an inner edge, an upper surface, a lower surface, and an outer edge surface extending from the leading edge to the trailing edge, each one of the pair of wing-shaped fairings including
an air intake located in said leading edge to supply free stream atmospheric air to a respective one of said pair of gas generators;
an air inlet connected to said air intake;
a curved duct connected to said air inlet, said curved duct turning the free stream atmospheric air towards said inner edge;
a particle separation outlet connected to an outer curved portion of said curved duct;
a channel particle outlet located in said trailing edge; and
a channel connecting said particle separation outlet to said channel particle outlet, wherein solid particles in said free stream atmospheric air follow a substantially straight path from said air intake through said outer curved portion to said particle separation outlet and then through said channel to said channel particle outlet.

5. The aircraft of claim 4 , further comprising said propulsor section having a central axis and said gas generator having a longitudinal axis at an angle to said central axis.

6. The aircraft of claim 4 , further comprising a wall surrounding at least a portion of each one of said pair of gas generators and said inner edges of each one of said pair of wing-shaped fairings blending into said wall.

7. An engine comprising:
a propulsor section having a free turbine and a fan driven by said free turbine;
a gas generator for generating a fluid for driving said free turbine;
an air intake for supplying free stream atmospheric air to said gas generator;
a wing-shaped fairing defined by a leading edge, a trailing edge, an inner edge, an upper surface, a lower surface, and an outer edge surface extending from the leading edge to the trailing edge;
an air inlet embedded within the wing-shaped fairing and connected to said air intake located in said leading edge;
a curved duct connected to the air inlet, said curved duct turning the free stream atmospheric air towards said inner edge and an outlet connected to an inlet of said gas generator;
a particle separation outlet connected to an outer curved portion of said curved duct;
a channel particle outlet located in said trailing edge; and
a channel connecting said particle separation outlet to said channel particle outlet, wherein solid particles in said free stream atmospheric air follow a substantially straight path from said air intake through said outer curved portion to said particle separation outlet and then through said channel to said channel particle outlet.

8. The engine of claim 7 , further comprising said free turbine and said fan rotating about a first axis and said gas generator having a longitudinal axis at an angle to said first axis.

9. The engine of claim 7 , wherein said gas generator comprises a reverse engine core.

10. The engine of claim 7 , further comprising a plenum for delivering said fluid to said free turbine and said plenum communicating with an outlet of said gas generator.

11. The propulsion system of claim 7 , wherein said air intake delivers said free stream atmospheric air to a compressor section of said gas generator.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M
• Zysman Steven H

Classifications

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title

• F02C7/052 Primary

  with dust-separation devices · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title