Abstract: An attachment mechanism for a gas turbine engine component includes an elongated body having at least first and second ends. A first attachment feature is formed at the first end. A second attachment feature is formed at the second end. The first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component. A fan section for a gas turbine engine and a gas turbine engine are also disclosed.

Abstract: 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.

Abstract: A thermal barrier attachment seal for a gas turbine engine component includes a spine having a first surface and a second surface facing opposite the first surface. A first layer of insulation is provided on the first surface. A second layer of insulation is provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component. A fan section for a gas turbine engine is also disclosed.

Abstract: A gas turbine engine anti-icing system troubleshooting method comprising providing an anti-icing system comprising a bleed air source coupled to a pressure regulating valve set having an upper valve coupled end-to-end in series with a lower valve; and an air pressure sensor coupled to the pressure regulating valve set downstream of the pressure regulating valve set; detecting at least one valve fault; checking the upper valve for the at least one valve fault; checking the lower valve for the at least one valve fault; deactivating at least one of the upper valve and the lower valve; and replacing at least one of the upper valve and lower valve.

Abstract: An attachment mechanism for a gas turbine engine component includes an elongated body having at least first and second ends. A first attachment feature is formed at the first end. A second attachment feature is formed at the second end. The first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component. A fan section for a gas turbine engine and a gas turbine engine are also disclosed.

Abstract: A thermal barrier attachment seal for a gas turbine engine component includes a spine having a first surface and a second surface facing opposite the first surface. A first layer of insulation is provided on the first surface. A second layer of insulation is provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component. A fan section for a gas turbine engine is also disclosed.