Gas turbine engine having a sensor assembly to detect torsional vibration

US12297743B2 · kind B2 · utility

Assignee

• General Electric Company · US

Inventors

• David Raju Yamarthi · Bengaluru, IN
• Tod Robert Steen · Cincinnati, US
• Ravindra Shankar Ganiger · Kanchinakote, IN
• Kudum Shinde · Kanchinakote, IN
• Ankita Sinha · Mountain View, US
• Aman Srivastava · Lucknow, IN
• Narayanan Payyoor · Thrissur, IN
• Venkata Subramanya Sarma Devarakonda · Savanuru, IN
• Rajesh Kumar Undipalli · Bengaluru, IN
• Dinesh Rakwal · Bengaluru, IN
• Himanshu Gupta · Bengaluru, IN
• Hrishi Ragesh · Bengaluru, IN

Key dates

• Filing date: Jul 31, 2023
• Grant date: May 13, 2025
• Expiry date: Jul 31, 2043

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2270/808
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

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.