DUCT RUPTURE DETECTION SYSTEM
A system for detecting a ruptured duct transporting a high-temperature fluid within a gas turbine engine is disclosed. In various embodiments, the system includes a rupture detection line configured to extend within a first fire zone of the gas turbine engine; one or more rupture sensing elements in electrical communication with and disposed along the rupture detection line, the one or more rupture sensing elements configured to detect a presence of a heated fluid having a heated fluid temperature less than a fire temperature; and a processor configured to monitor the one or more rupture sensing elements.
1 . A system for detecting a ruptured duct transporting a high-temperature fluid within a gas turbine engine, comprising:
a rupture detection line configured to extend within a first fire zone of the gas turbine engine;
a plurality of rupture sensing elements in electrical communication with and disposed along the rupture detection line, the plurality of rupture sensing elements configured to detect a presence of a heated fluid having a heated fluid temperature less than a fire temperature; and
a processor configured to monitor the plurality of rupture sensing elements.
2 . The system of claim 1 , wherein the rupture detection line is configured to extend into a second fire zone.
3 . The system of claim 2 , wherein the rupture detection line includes a first section configured to detect a rupture of a first duct in the first fire zone and a second section configured to detect the rupture of a second duct in the second fire zone.
4 . The system of claim 3 , wherein the first duct is at least one of a cooling air duct, an environmental air duct, a de-icing duct and an oil duct.
5 . The system of claim 3 , wherein the second duct is at least one of an environmental air duct and a de-icing duct.
6 . The system of claim 2 , wherein the rupture detection line includes a first section configured to detect a rupture of a first duct in the first fire zone and a second section configured to detect a flow of the heated fluid from the first duct into the second fire zone.
7 . The system of claim 6 , wherein the first duct is one of a cooling air duct and an environmental air duct.
8 . The system of claim 1 , wherein the rupture detection line includes a first section within the first fire zone and a second section within a second fire zone.
9 . The system of claim 8 , wherein the plurality of rupture sensing elements includes a first rupture sensing element disposed on the first section and a second rupture sensing element disposed on the second section.
10 . The system of claim 9 , wherein the first fire zone is a core compartment and the second fire zone is a pylon.
11 . The system of claim 9 , wherein the first rupture sensing element includes a first thermistor configured to detect a first temperature and the second rupture sensing element includes a second thermistor configured to detect a second temperature.
12 . The system of claim 11 , wherein the first temperature is characteristic of a heated gas bled from a high pressure compressor of the gas turbine engine.
13 . A gas turbine engine, comprising:
a compressor section;
a duct configured to bleed air from the compressor section, the duct having at least a portion disposed within a first fire zone of the gas turbine engine;
a rupture detection line configured to extend within the first fire zone;
a plurality of rupture sensing elements in electrical communication with and disposed along the rupture detection line, the plurality of rupture sensing elements configured to detect a presence of a heated fluid escaping from the duct, the heated fluid having a heated fluid temperature less than a fire temperature; and
a processor configured to monitor the plurality of rupture sensing elements.
14 . The gas turbine engine of claim 13 , wherein the rupture detection line is configured to extend into a second fire zone.
15 . The gas turbine engine of claim 14 , wherein the first fire zone is a core compartment and the second fire zone is a pylon.
16 . The gas turbine engine of claim 15 , wherein the rupture detection line includes a first section within the first fire zone and a second section within the second fire zone and wherein the plurality of rupture sensing elements includes a first rupture sensing element disposed on the first section and a second rupture sensing element disposed on the second section.
17 . The gas turbine engine of claim 16 , wherein the first sensing element includes a first thermistor configured to detect a first temperature and the second rupture sensing element includes a second thermistor configured to detect a second temperature.
18 . The gas turbine engine of claim 17 , wherein the first temperature is characteristic of a heated gas bled from a high pressure compressor of the gas turbine engine.
19 . A thermal detection system for an aircraft, comprising:
a fire detection system having a fire detection line disposed within a first fire zone of a gas turbine engine, a fire sensing element configured to detect a fire occurring within the first fire zone and a first processor configured to monitor the fire sensing element; and
a duct rupture detection system having a rupture detection line disposed within the first fire zone, a rupture sensing element in electrical communication with and disposed along the rupture detection line, the rupture sensing element configured to detect a presence of a heated fluid having a heated fluid temperature less than a fire temperature, and a second processor configured to monitor the rupture sensing element.
20 . The thermal detection system of claim 19 , wherein the rupture detection line includes a first section configured to detect a ruptured duct in the first fire zone and a second section configured to detect a flow of the heated fluid from the ruptured duct into a second fire zone.