Method for detecting a fluid leak in a turbomachine and fluid distribution system

Patent metadata

Field	Value
Publication number	US-10345190-B2
Application number	US-201515537745-A
Country	US
Kind code	B2
Filing date	Dec 22, 2015
Priority date	Dec 24, 2014
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A method for detecting a high temperature fluid leak in a turbomachine. The turbomachine includes a source of high temperature pressurized fluid, at least one fluid distribution line suitable for distributing said high temperature fluid, and a turbomachine compartment wherein the distribution line is at least partially housed. The method includes measuring at least two pressure parameters of the turbomachine compartment, including a measured pressure and a pressure variation over time; detecting a high temperature fluid leak when at least one of the two pressure parameters of the turbomachine compartment reaches a characteristic value of a high-temperature fluid leak in the compartment. A high-temperature fluid distribution system and a turbomachine comprising such a high temperature fluid distribution system.

First claim

The invention claimed is:

1. A leak detecting method of a high temperature fluid in an aircraft turbomachine, said turbomachine including a pressurised high temperature fluid source producing the high temperature fluid, at least one fluid distribution line distributing said high temperature fluid to different parts of the turbomachine and/or an aircraft including said turbomachine, and a turbomachine zone, wherein the fluid distribution line is at least partly housed in the turbomachine zone, said turbomachine zone having in use of the turbomachine a pressure lower than a temperature of the high temperature fluid, the method comprising:
measuring at least a first and a second pressure parameters of the turbomachine zone, the first pressure parameter corresponding to measured pressure and the second pressure parameter corresponding to a pressure variation over time; and
detecting a high temperature fluid leak when at least one of the first and the second pressure parameter of the turbomachine zone is equal or greater than a first and a second threshold value of a high temperature fluid leak in the turbomachine zone respectively.

2. The leak detecting method according to claim 1 ,
wherein the first parameter is a measure pressure selected from a group including an absolute pressure of the turbomachine zone, a relative pressure of the turbomachine zone with respect to the atmospheric pressure, and a differential pressure representative of the difference between the pressure in the turbomachine zone and the pressure of a reference area, and
wherein detecting the high temperature fluid leak when the first pressure parameter is equal or greater than the first pressure threshold value of a high temperature fluid leak in the turbomachine zone.

3. The leak detecting method according to claim 1 , wherein detecting the high temperature fluid when the second pressure parameter is equal or greater than the second variation threshold value of a high temperature fluid leak in the turbomachine zone.

4. The leak detecting method according to claim 1 , wherein said turbomachine zone is sealingly insulated with respect to the high temperature fluid distributed by the at least one fluid distribution line.

5. The leak detecting method according to claim 1 for an aircraft including at least one second turbomachine having a second turbomachine zone, wherein said first pressure parameter is based on a pressure comparison between the pressure of the turbomachine zone and the second turbomachine zone, detecting the leak when the turbomachine zone pressure is higher by the first threshold value than the pressure of the second turbomachine zone of the second turbomachine, said first threshold value being a high temperature fluid leak in the turbomachine zone of the first turbomachine.

6. The leak detecting method according to claim 1 , further comprising:
closing said at least one fluid distribution line when a leak is detected.

7. The leak detecting method according to claim 1 , wherein the turbomachine zone is radially located between a fan casing and a cowling of a nacelle of the turbomachine.

8. The leak detecting method according to claim 1 , wherein the high temperature fluid is air from a compressor of the turbomachine, said at least one fluid distribution line including a first and a second fluid distribution line, the first fluid distribution line distributing air to the aircraft and a starter of the turbomachine, the second fluid distribution line distributing air at an air intake duct of the turbomachine to feed an anti-icing system, the first and the second fluid distribution line being at least partly housed in the turbomachine zone.

9. The leak detecting method according to claim 1 , wherein said one fluid distribution line includes at least a first and a second fluid distribution lines for distributing the high temperature fluid, both the first and the second fluid distribution lines being at least partly housed in the turbomachine zone, the method further comprising:
closing the first and the second fluid distribution lines when a fluid leak is detected.

10. A high temperature fluid distribution system for an aircraft turbomachine, the system comprising:
a pressurised high temperature fluid source providing the high temperature fluid;
at least one distribution line for high temperature fluid, the at least one distribution line distributing said high temperature fluid to different parts of the turbomachine and/or an aircraft including said turbomachine;
a turbomachine zone, wherein the at least one fluid distribution line is at least partly housed in the turbomachine zone, said turbomachine zone having in use of the turbomachine a pressure lower than the pressure of the high temperature fluid;
at least one pressure sensor configured to measure two pressure parameters of the turbomachine zone including a measured pressure and a pressure variation over time; and
an engine calculator configured to receive the measured two pressure parameters, engine calculator being configured to detect a high temperature fluid leak when at least one of the measured two pressure parameters of the turbomachine zone is equal or greater than a threshold value of a high temperature fluid leak in the turbomachine zone.

11. The high temperature fluid distribution system according to claim 10 , wherein said turbomachine zone is sealingly insulated with respect to the fluid distributed by the at least one distribution line, and has an internal volume higher than twice a total volume of a part of the at least one line being housed in the turbomachine zone.

12. The fluid distribution system according to claim 10 , wherein said turbomachine zone is closed and contains an air volume higher than twice a total volume of a part of the at least one line being housed in the turbomachine zone.

13. The high temperature fluid distribution system according to claim 10 , wherein said turbomachine zone comprises at least one element of composite material(s) with a temperature resistance insufficient to withstand the fluid high temperature beyond a predetermined delay lower than 30 seconds.

14. The high temperature fluid distribution system according to claim 13 , wherein said element of composite material(s) consists of a turbomachine zone wall adjacent to an air volume through which at least one fluid distribution line passes.

15. A turbomachine comprising:
a high temperature fluid distribution system, wherein the system includes
a pressurised high temperature fluid source providing the high temperature fluid;
at least one distribution line distributing said high temperature fluid to different parts of the turbomachine and/or an aircraft including said turbomachine;
a turbomachine zone, wherein the at least one fluid distribution line is at least partly housed in the turbomachine zone, said turbomachine zone having in use of the turbomachine a pressure lower than the pressure of the high temperature fluid;
at least one pressure sensor configured to measure two pressure parameters of the turbomachine zone including a measured pressure and a pressure variation over time; and
an engine calculator configured to receive the measured two pressure parameters, the engine calculator being configured to detect a high temperature fluid leak when at least one of the measured two pressure parameters of the turbomachine zone is equal or greater than a threshold value of a high temperature fluid leak in the turbomachine zone.

Assignees

• Safran Aircraft Engines

Inventors

• Everwyn Alexandre Patrick Jacques Roger
• Rodhain Arnaud

Classifications

• B64D13/08

  the air being heated or cooled · CPC title

• B64D2013/0607

  providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows · CPC title

• F05D2270/309

  Rate of change of parameters · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• F02C9/24

  Control of the pressure level in closed cycles · CPC title