	US 12,352,178 B2
	Turbine overspeed protection
Andrew Parsley, Bristol (GB); and Natalie C Wong, Bristol (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Apr. 3, 2024, as Appl. No. 18/625,769.
Claims priority of application No. 2306521 (GB), filed on May 3, 2023.
Prior Publication US 2024/0368999 A1, Nov. 7, 2024
Int. Cl. F01D 21/14 (2006.01); F01D 17/02 (2006.01); F01D 17/04 (2006.01); F01D 17/06 (2006.01); F01D 17/10 (2006.01); F01D 21/00 (2006.01); F01D 21/02 (2006.01); F01D 21/04 (2006.01); F01D 21/06 (2006.01); F02C 3/13 (2006.01); F02C 6/08 (2006.01); F02C 6/18 (2006.01); F02C 9/18 (2006.01); F02C 9/24 (2006.01); F04D 27/00 (2006.01); F04D 27/02 (2006.01)

CPC F01D 21/14 (2013.01) [F01D 17/02 (2013.01); F01D 17/04 (2013.01); F01D 17/06 (2013.01); F01D 17/105 (2013.01); F01D 21/003 (2013.01); F01D 21/02 (2013.01); F01D 21/04 (2013.01); F01D 21/06 (2013.01); F02C 3/13 (2013.01); F02C 6/08 (2013.01); F02C 6/18 (2013.01); F02C 9/18 (2013.01); F02C 9/24 (2013.01); F04D 27/009 (2013.01); F04D 27/0207 (2013.01); F04D 27/0238 (2013.01); F05D 2270/09 (2013.01); F05D 2270/3015 (2013.01)]

15 Claims

1. An apparatus for reducing a pressure differential across a turbine of a gas turbine engine during a shaft break event in which a shaft of the gas turbine engine breaks, the apparatus comprising:

a pressure equalization apparatus configured to introduce a pressurized fluid into a core airflow at a region (i) downstream of the turbine and (ii) forward of an exhaust nozzle in the event of the shaft break event to, without combustion of the pressurized fluid, directly and near-instantaneously increase a local pressure at the downstream region of the turbine and thereby reduce the pressure differential across the turbine;

a sensor configured to directly detect the shaft break event; and

a control system connected to the sensor,

wherein the control system is configured to activate the pressure equalization apparatus when the sensor directly detects the shaft break event.