Device for distributing fuel flows for a fuel supply circuit of a turbomachine combustion chamber

Patent metadata

Field	Value
Publication number	US-2023392550-A1
Application number	US-202118248666-A
Country	US
Kind code	A1
Filing date	Oct 5, 2021
Priority date	Oct 14, 2020
Publication date	Dec 7, 2023
Grant date	—

Abstract

A device for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbo machine, in particular of an aircraft, the device including a rotating main body extending about a longitudinal axis, the main body including an internal flow duct for a first flow of fuel, extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second flow of fuel, and including at least one orifice for the second flow of fuel to pass through, and an external annular groove in fluidic communication with the at least one orifice in the first portion.

First claim

1 . A distribution device of at least one fuel flow for a fuel supply circuit of a combustion chamber of a turbomachine, in particular an aircraft, the device comprising a main body of revolution extending about a longitudinal axis, the main body comprising:
an internal conduit for the flow of a first fuel flow and extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second fuel flow, and comprising at least one passage orifice for the second fuel flow, and an external annular gorge in fluid communication with said at least one orifice of the first portion, and a second annular portion ( 83 ) configured to form an inlet passage for the first fuel flow (F 1 ) through the internal conduit ( 800 )
Characterized in that the second portion ( 83 ) comprises an annular collar ( 84 ) extending radially about the axis (A).

2 . The device according to claim 1 , wherein said at least one passage orifice of the second fuel flow is distributed in an annular row of orifices.

3 . The device according to claim 2 , wherein the annular row of orifices each extend along an axis parallel to the axis.

4 . (canceled)

5 . The device according to claim 1 , wherein the second portion is connected to the first portion via an intermediate portion of the distribution device delimiting at least partly the internal conduit.

6 . (canceled)

7 . The device according to claim 1 , wherein the annular gorge is delimited at least partly by a flank of the collar and a wall of the first portion.

8 . The device according to claim 1 , wherein the second portion further comprises at least one annular sealing and attaching groove configured for mounting a sealing element.

9 . The device according to claim 1 , wherein the first annular portion has an external diameter (D 81 ) smaller than an external diameter (D 84 ) of the annular collar of the second annular portion.

10 . The device according to claim 1 , wherein each orifice in the annular row of orifices has a diameter (D 810 ) of between 3 and 10 mm, preferably between 5 and 7 mm, and still more preferably of about 5.5 mm.

11 . The device according to claim 2 , wherein the annular row of orifices comprises between five and twenty orifices, preferably between fifteen and twenty orifices, and even more preferably about seventeen orifices.

12 . A turbomachine, in particular an aircraft turbomachine, comprising a distribution device of at least one fuel flow according to claim 1 , for a fuel supply circuit of a combustion chamber of the turbomachine.

Assignees

• Safran Aircraft Engines

Inventors

• Le Normand Kevin Didier Pierre
• Brettes Frederic
• Pora Loic

Classifications

• F23R3/283 Primary

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

• F23R3/34

  Feeding into different combustion zones · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C7/222 Primary

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