| CPC F01D 21/003 (2013.01) [G01M 3/26 (2013.01); G01M 15/14 (2013.01); G07C 5/008 (2013.01); F05D 2260/83 (2013.01)] | 20 Claims |
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1. An assembly for an aircraft propulsion system, the assembly comprising:
a high-pressure turbine forming a core flow path;
a low-pressure turbine further forming the core flow path, the low-pressure turbine disposed downstream of the high-pressure turbine;
a mid-turbine frame disposed between the high-pressure turbine and the low-pressure turbine, the mid-turbine frame including an outer case, an inner case, an inter-turbine duct, and a plurality of frame seals, the outer case, the inner case, the inter-turbine duct, and the plurality of frame seals forming a mid-turbine frame cavity of the mid-turbine frame, the plurality of frame seals configured to seal the mid-turbine frame cavity, the inter-turbine duct further forming the core flow path;
a pressurized air source fluidly coupled to the mid-turbine frame, the pressurized air source configured to direct pressurized air into the mid-turbine frame cavity;
a first pressure sensor in fluid communication with the mid-turbine frame cavity, the first pressure sensor configured to measure a first pressure within the mid-turbine frame cavity; and
an engine control system connected in signal communication with the first pressure sensor, the engine control system including a processor in communication with a non-transitory memory storing instructions which, when executed by the processor, cause the processor to:
measure the first pressure using the first pressure sensor; and
identify a presence or an absence of an increased wear condition of the plurality of frame seals by comparing the first pressure to a pressure threshold value, the presence of the increased wear condition identified where the first pressure is less than the pressure threshold value.
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