Method for detecting a fluid leak in a turbomachine and system for distributing a fluid
First Claim
1. A method for detecting a fluid leak in an aircraft turbomachine, the turbomachine including:
- a high temperature gas fluid source which provides high temperature gas fluid, a temperature of the high gas fluid being greater than 350°
C.,at least one gas fluid distribution pipe adapted to distribute the gas fluid to different parts of the turbomachine and/or an aircraft which is to be equipped with the turbomachine, anda turbomachine compartment in which the distribution pipe is at least partly accommodated, the compartment containing air which has in operation a temperature lower to the temperature of the gas fluid, the air of the compartment also having a pressure lower than a pressure of the gas fluid, the turbomachine compartment including a temperature sensor in at least one location outside the at least one gas fluid distribution pipe and remote from the at least one gas fluid distribution pipe, the turbomachine compartment being radially situated between a fan casing and a nacelle of the turbomachine,the method comprising;
measuring, using the temperature sensor, a temporal temperature variation of the air in the at least one location in the compartment between two temporal instants to obtain a temperature gradient;
detecting, using processing circuitry, a gas fluid leak in the compartment when the temperature gradient is greater than or equal to a threshold temperature gradient; and
closing the at least one gas fluid pine upstream the compartment when the gas fluid leak is detected.
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Accused Products
Abstract
A system and method for detecting a fluid leak in a turbomachine. The turbomachine includes a high temperature fluid source, at least one fluid distribution pipe adapted to distribute the fluid to different parts of the turbomachine and/or an aircraft which is to be equipped with the turbomachine, a turbomachine compartment in which the distribution pipe is at least partly accommodated, the compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method includes measuring a temperature variation in the compartment between two instants to obtain a temperature gradient, and detecting a fluid leak when the temperature gradient is greater than or equal to a threshold temperature gradient.
54 Citations
13 Claims
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1. A method for detecting a fluid leak in an aircraft turbomachine, the turbomachine including:
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a high temperature gas fluid source which provides high temperature gas fluid, a temperature of the high gas fluid being greater than 350°
C.,at least one gas fluid distribution pipe adapted to distribute the gas fluid to different parts of the turbomachine and/or an aircraft which is to be equipped with the turbomachine, and a turbomachine compartment in which the distribution pipe is at least partly accommodated, the compartment containing air which has in operation a temperature lower to the temperature of the gas fluid, the air of the compartment also having a pressure lower than a pressure of the gas fluid, the turbomachine compartment including a temperature sensor in at least one location outside the at least one gas fluid distribution pipe and remote from the at least one gas fluid distribution pipe, the turbomachine compartment being radially situated between a fan casing and a nacelle of the turbomachine, the method comprising; measuring, using the temperature sensor, a temporal temperature variation of the air in the at least one location in the compartment between two temporal instants to obtain a temperature gradient; detecting, using processing circuitry, a gas fluid leak in the compartment when the temperature gradient is greater than or equal to a threshold temperature gradient; and
closing the at least one gas fluid pine upstream the compartment when the gas fluid leak is detected. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A system for distributing a high temperature gas fluid for an aircraft turbomachine adapted to detect a fluid leak of the high temperature gas fluid in a turbomachine compartment of the aircraft turbomachine, the system comprising:
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a high temperature gas fluid source which provides high temperature gas fluid, a temperature of the high gas fluid being greater than 350°
C.;at least one fluid distribution pipe adapted to distribute the gas fluid to different parts of the turbomachine and/or the aircraft; the turbomachine compartment in which the distribution pipe is at least partly accommodated, said compartment containing air which has in operation a temperature lower to a temperature the gas fluid, the air of the compartment also having in operation a pressure lower than a pressure of the gas fluid, the turbomachine compartment being radially situated between a fan casino and a nacelle of the turbomachine; at least one temperature sensor of the turbomachine compartment in at least one location outside the at least one gas fluid distribution pipe and remote from the at least one gas fluid distribution pipe; a dosing valve of the one fluid distribution pipe upstream to the compartment; and processing circuitry arranged to control the at least one temperature sensor and configured to detect a gas fluid leak in the compartment, wherein the processing circuitry is configured to supply, from the at least one temperature sensor, a measurement of a temporal temperature variation of the air at at least one location in the compartment between two temporal instants in order to deduce therefrom a temperature gradient, and to detect the gas fluid leak when the temperature gradient is greater than and/or equal to a threshold temperature gradient, and wherein the processing circuitry is further configured to close the closing valve when the gas fluid leak is detected in order to close the at least one gas fluid pipe upstream the compartment. - View Dependent Claims (13)
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Specification