IP Library Granted Patent US 7,896,260
Granted Patent B2
US 7,896,260 · App. 12/016,480 · Granted Mar 1, 2011

Two-stage fuel injector

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Quick Facts
Patent No.
US 7,896,260
App. No.
12/016,480
Granted
Mar 1, 2011
Kind
B2
Abstract

This injector with two valves ( 7, 10 ) which open at different fuel pressures so as to establish a primary flow regime and then a secondary flow regime is characterized in that the primary regime is enriched with fuel via an orifice ( 21 ) which adds a branch to the primary flow path of the fuel, but which is closed when the secondary valve is displaced so as to prevent enrichment of the fuel in the secondary regime. This invention applies in particular to certain aircraft engines.

Claims (11)

1. A two-stage fuel injector comprising:

two valves arranged in series and biased towards closed positions, said two valves including a primary valve arranged on a primary fuel path and a secondary valve arranged on a secondary fuel path, the primary fuel path and the secondary fuel path branching downstream of the primary valve,

inner body in which the secondary valve slides and which delimits the primary path, the primary path surrounding the inner body,

wherein the secondary path comprises a central cavity of the secondary valve and at least one hole passing radially through the secondary valve between a periphery and the central cavity,

at least one orifice passing through the inner body between the primary fuel path and the secondary valve and opening into the hole and immediately downstream a solid portion of the secondary valve when the secondary valve is in the closed position, and

wherein said orifice is closed off by the secondary valve as soon as said secondary valve is displaced when the secondary flow is established so that an enrichment of a mixture delivered by said injector ceases.

2. A two-stage fuel injector according to claim 1 , wherein the primary circuit comprises at least one orifice passing through a collar of the inner body which extends as far as a peripheral bushing of the injector.

3. A combustion chamber equipped with at least one adjuster according to claim 1 .

4. A gas turbine comprising a combustion chamber according to claim 3 .

5. A two-stage fuel injector according to claim 1 , wherein said primary flow path passes around said primary valve and then around the inner body and into an annular slot located between the inner body and an outer bushing for said injector, and wherein said annular slot is interrupted by a collar of the inner body which extends as far as the outer bushing.

6. A two-stage fuel injector according to claim 5 , wherein the primary fuel flow path is re-established by an orifice passing through said collar and joining two portions of the annular slot.

Assignments (2)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →