Cooled fuel injector system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10739005-B2
Application number	US-201414912117-A
Country	US
Kind code	B2
Filing date	Aug 14, 2014
Priority date	Aug 16, 2013
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut. A gas turbine engine is provided that includes a multiple of fuel injectors in communication with a combustor and a cooling system in communication with each of the multiple of fuel injectors.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a combustor;
a multiple of fuel injectors in communication with said combustor;
a cooling fluid manifold in communication with each of said multiple of fuel injectors, said cooling fluid manifold comprising an intake plenum and an exhaust plenum separated by a barrier, wherein said intake plenum and said exhaust plenum communicates with said multiple of fuel injectors, wherein said cooling fluid manifold is a circular internal split manifold;
an inlet passage in communication with said cooling fluid manifold;
an inlet scoop to direct a portion of an airflow into said inlet passage; and
an exhaust passage in communication with said cooling fluid manifold for discharging the airflow.

2. The gas turbine engine as recited in claim 1 , further comprising a diffuser case module, said multiple of fuel injectors mounted to said diffuser case module.

3. The gas turbine engine as recited in claim 1 , further comprising a heat exchanger operatively associated with said inlet passage for reducing a temperature of fluid flowing in said inlet passage.

4. The gas turbine engine as recited in claim 1 , wherein said airflow is a bypass airflow.

5. The gas turbine engine as recited in claim 4 , wherein said inlet scoop is located through a core nacelle axially upstream of a throat region between said core nacelle and a fan nacelle.

6. The gas turbine engine as recited in claim 1 , further comprising an inlet passage in communication with said cooling fluid manifold and a compressor section of said gas turbine engine.

7. The gas turbine engine as recited in claim 1 , further comprising an inlet passage in communication with said cooling fluid manifold and a 2.5 bleed compartment.

8. The gas turbine engine as recited in claim 1 , further comprising an exhaust from said exhaust passage located through a core nacelle axially downstream of a throat region between said core nacelle and a fan nacelle.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Kironn Lexia
• Coffey Roger O
• Twelves Wendell V
• Schirtzinger Gary A
• Ott Joe
• Butcher Evan
• Frish John D

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F23R3/20

  incorporating fuel injection means · CPC title

• F23K2300/20

  Supply line arrangements · CPC title

• F23R3/283 Primary

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title