Aircraft turbine engine assembly comprising a passive valve for by-passing a fuel/oil heat exchanger

Patent metadata

Field	Value
Publication number	US-12158109-B2
Application number	US-202118253791-A
Country	US
Kind code	B2
Filing date	Nov 30, 2021
Priority date	Dec 1, 2020
Publication date	Dec 3, 2024
Grant date	Dec 3, 2024

Abstract

An aircraft turbine engine assembly, including a lubricating oil circuit and a fuel supply device, the assembly also including a passive bypass valve enabling the oil to bypass an exchanger, the valve including a valve body and a piston arranged to move in a sliding space defining a first actuating chamber supplied with oil from the oil circuit, as well as a second actuating chamber supplied with fuel from the device, the valve being configured so that when the differential pressure between the oil pressure in the first actuating chamber and the fuel pressure in the second actuating chamber drops below a predetermined value of differential pressure, the piston moves from a normal operating position to an exchanger bypass position.

First claim

The invention claimed is:

1. An aircraft turbine engine assembly, comprising:
a lubricating oil circuit;
a fuel supply device;
a fuel/oil heat exchanger that is in common with the lubricating oil circuit and the fuel supply device; and
a passive bypass valve enabling a lubricating oil of the lubricating oil circuit to bypass the fuel/oil heat exchanger, the passive bypass valve comprising a valve body and a piston configured to be movable in a sliding space formed in the valve body, the sliding space and a first side of the piston defining a first actuating chamber supplied with the lubricating oil from the lubricating oil circuit, and the sliding space and a second side of the piston defining a second actuating chamber supplied with a fuel from the fuel supply device,
the piston of the passive bypass valve being configured to have a normal operating position allowing the lubricating oil of the lubricating oil circuit to flow to the fuel/oil heat exchanger via the passive bypass valve and a bypass position prohibiting the lubricating oil of the lubricating oil circuit from flowing to the fuel/oil heat exchanger, and when a pressure difference between an oil pressure of the lubricating oil in the first actuating chamber and a fuel pressure of the fuel in the second actuating chamber drops below a predetermined pressure difference value, the piston moves from the normal operating position to the bypass position.

2. The aircraft turbine engine assembly according to claim 1 , wherein the passive bypass valve further includes an elastic return means forcing the piston towards the bypass position.

3. The aircraft turbine engine assembly according to claim 1 , wherein the passive bypass valve is a spool piston valve.

4. The aircraft turbine engine assembly according to claim 3 , wherein the piston of the passive bypass valve isa spool piston, wherein the passive bypass valve comprises:
a first annular oil passage and a second annular oil passage axially separated from each other;
each of a first oil inlet and a first oil outlet fluidly connected to the sliding space of the valve body, the first oil outlet fluidly connected to an oil intake of the fuel/oil heat exchanger, and the first oil inlet and the first oil outlet fluidly connected to each other via the first annular oil passage when the spool piston moves to the normal operating position; and
each of a second oil inlet and a second oil outlet fluidly connected to the sliding space of the valve body, the second oil inlet fluidly connected to an oil exhaust of the fuel/oil heat exchanger, and the second oil inlet and the second oil outlet fluidly connected to each other via the second annular oil passage when the spool piston moves to the normal operating position; and
wherein, when the spool piston moves to the bypass position:
the first oil inlet and the first oil outlet fluidly disconnects;
the second oil inlet and the second oil outlet fluidly disconnects; and
the first oil inlet and the second oil outlet fluidly connects via the second annular oil passage.

5. The aircraft turbine engine assembly according to claim 1 , wherein the passive bypass valve further includes a third oil inlet fluidly connected to the first actuating chamber, and a fuel inlet fluidly connected to the second actuating chamber.

6. The aircraft turbine engine assembly according to claim 5 , wherein the fuel inlet of the passive bypass valve is fluidly connected to both of the second actuating chamber and a fuel intake of the fuel/oil heat exchanger, or the fuel inlet of the passive bypass valve is fluidly connected to both of the second actuating chamber and a fuel exhaust of the fuel/oil heat exchanger.

7. The aircraft turbine engine assembly according to claim 1 , wherein the passive bypass valve further includes a position sensor for the piston in the sliding space of the valve body.

8. The aircraft turbine engine assembly according to claim 1 , wherein the lubricating oil circuit further comprises at least one enclosure to be lubricated.

9. An aircraft turbine engine comprising the aircraft turbine engine assembly according to claim 1 .

10. The aircraft turbine engine assembly according to claim 2 , wherein the elastic return means is a compression spring.

11. The aircraft turbine engine assembly according to claim 8 , wherein the at least one enclosure to be lubricated is at least one of a roller bearing enclosure or an oil enclosure of the accessory gearbox.

12. The aircraft turbine engine according to claim 9 , wherein the aircraft turbine engine is a turbojet engine.

Assignees

• Safran Aircraft Engines

Inventors

• Oriol Sébastien
• Cotereau Nicolas Vincent Pierre-Yves
• Boutaleb Mohammed-Lamine

Classifications

• F16K17/082

  with piston · CPC title

• F28F2265/06

  by using means for draining heat exchange media from heat exchangers · CPC title

• F28F27/02

  for controlling the distribution of heat-exchange media between different channels ({static flow control means in header boxes F28F9/026}; arrangements of guide plates or guide vanes F28F9/22, F28F25/12) · CPC title

• F28F2265/16

  for preventing leakage · CPC title

• F16K17/046

  the valve being of the gate valve type or the sliding valve type · CPC title