Spool for fuel circuit valve of an aircraft engine

Patent metadata

Field	Value
Publication number	US-10690264-B2
Application number	US-201716095187-A
Country	US
Kind code	B2
Filing date	Apr 20, 2017
Priority date	Apr 21, 2016
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.

First claim

The invention claimed is:

1. A spool for a valve of an aircraft engine fuel circuit extending along a longitudinal axis, the spool comprising:
a narrowed intermediate portion extending between first and second cylindrical end portions, the first cylindrical end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged perpendicular to the longitudinal axis overall, the narrowed intermediate portion including, as an extension of the shoulder, a cylindrical section,
wherein the shoulder is provided with a step which is a protuberance protruding with respect to said shoulder as an extension of a cylindrical surface of the first cylindrical end portion and which, when fuel flows along the first cylindrical end portion in a direction of the narrowed intermediate portion and of the second cylindrical end portion, ensures generation of a fuel jet on the cylindrical section of the narrowed intermediate portion, a recirculation of fuel forming in a recirculation zone adjoining said shoulder, and
wherein the shoulder comprises a groove which extends radially from the cylindrical surface of the first cylindrical end portion, in a direction of the longitudinal axis, and from which extends the step, so as to accelerate the recirculation of the fuel in the recirculation zone.

2. The spool according to claim 1 , wherein the step extends substantially perpendicularly from the surface of the shoulder.

3. The spool according to claim 1 , wherein the groove extends longitudinally from the shoulder on the cylindrical section of the narrowed intermediate portion and wherein the groove has, at said cylindrical section, a flat bottom overall, the fuel jet generated by the groove reaching said cylindrical section at the bottom of said groove.

4. A valve for an aircraft engine fuel circuit, comprising:
a sleeve, in an interior of which is provided a spool according to claim 1 , said sleeve comprising two control chambers between which the spool extends and an intermediate chamber provided with a fuel inlet and a fuel outlet wherein the first and the second cylindrical end portions and the narrowed intermediate portion of the spool extend, the spool being configured to be displaced relative to the sleeve under an influence of a pressure difference between the two control chambers, between a closed position wherein the spool blocks the fuel inlet, and an open position wherein the spool frees the fuel inlet.

5. An aircraft turbomachine fuel circuit comprising a valve according to claim 4 .

6. An assembly comprising an aircraft turbomachine and a fuel circuit according to claim 5 .

7. An aircraft comprising a turbomachine connected to a fuel circuit according to claim 5 .

8. The spool according to claim 1 , wherein the narrowed intermediate portion includes a frustoconical portion connecting the cylindrical section to the second cylindrical end portion.

9. The spool according to claim 3 , wherein the groove incudes a fillet between the flat bottom and a surface of the groove disposed perpendicular to the longitudinal axis and set back from the shoulder with respect to the second cylindrical end portion.

Assignees

• Safran Aircraft Engines

Inventors

• Bernard Clement
• Pora Loic
• Cebille Christophe

Classifications

• F16K11/0708 Primary

  comprising means to avoid jamming of the slide or means to modify the flow · CPC title

• F15B13/0402

  for linearly sliding valves, e.g. spool valves · CPC title

• F16K31/0613

  with cylindrical slides · CPC title

• F16K47/08 Primary

  for decreasing pressure {or noise level} and having a throttling member separate from the closure member {, e.g. screens, slots, labyrinths} · CPC title

• Y10T137/8671

  With annular passage [e.g., spool] · CPC title