General Electric Company

Himanshu Gupta

Ravindra Shankar Ganiger

David Raju Yamarthi

Deepak Trivedi

Steven Douglas Johnson

Narayanan Payyoor

Kudum Shinde

Vidyashankar Ramasastry Buravalla

Tod Robert Steen

Narendra Anand Hardikar

Prateek Jalan

Shalini Thimmegowda

Ankita Sinha

Grant Robert Portune

Amit Goyal

Srinivasan Swaminathan

Venkata Subramanya Sarma Devarakonda

Guru Venkata Dattu Jonnalagadda

Chandrashekhar Kandukuri

Rajesh Kumar Undipalli

Shalabh Saxena

Hrishi Ragesh

Aman Srivastava

Dinesh Rakwal

A gas turbine engine includes a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine, an airflow passage having a core passage and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.

Gas turbine engine having a sensor assembly to detect torsional vibration

A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

Seal support assembly for a turbine engine

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Bengaluru, India

Himanshu Gupta