Turbine engine fuel injector with permanent leakage flow

Patent metadata

Field	Value
Publication number	US-9494079-B2
Application number	US-201314378797-A
Country	US
Kind code	B2
Filing date	Feb 12, 2013
Priority date	Feb 24, 2012
Publication date	Nov 15, 2016
Grant date	Nov 15, 2016

Abstract

A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit.

First claim

The invention claimed is:

1. A fuel injector for a turbine engine or an airplane turboprop or turbojet, the fuel injector comprising:
a body including an admission orifice for admitting fuel under pressure;
a stop valve mounted in the body downstream from the admission orifice and configured to open at a first determined fuel pressure and to remain open beyond the first determined fuel pressure to feed a primary fuel circuit;
a metering valve mounted in the body downstream from the stop valve and configured to open beyond a second determined fuel pressure greater than the first determined fuel pressure, and to remain open beyond the second determined fuel pressure to feed a secondary fuel circuit;
a tubular support radially surrounding the metering valve, the metering valve configured to slide within the tubular support; and
at least one leakage channel extending in the tubular support from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary fuel circuit.

2. The fuel injector according to claim 1 , wherein the at least one leakage channel is formed as a coil or a labyrinth.

3. The fuel injector according to claim 2 , wherein the at least one leakage channel is of helical or spiral shape.

4. The fuel injector according to claim 3 , wherein the at least one leakage channel extends around an axis coinciding with an axis of the metering valve.

5. The fuel injector according to claim 3 , wherein the at least one leakage channel includes a thread on a cylindrical surface of the tubular support.

6. The fuel injector according to claim 3 , wherein a helical groove is formed in an outer wall of the tubular support, a bushing surrounds the tubular support to cover the helical groove, and the at least one leakage channel comprises two ends that open out, respectively, upstream and downstream from the metering valve.

7. The fuel injector according to claim 1 , wherein the tubular support comprises a hole offset relative to an axis of the metering valve, the at least one leakage channel formed in an insert housed within the hole.

8. A turbine engine or an airplane turboprop or turbojet comprising at least one fuel injector according to claim 1 .

Assignees

• Snecma

Inventors

• Pousseo Emilie Charlotte
• Rodrigues Jose Roland

Classifications

• F23N2235/24

  Valve details · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F02C7/232 Primary

  Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23K2900/05141

  Control or safety devices in liquid fuel supply line · CPC title