公开(公告)号：US12152542B2

公开(公告)日：2024-11-26

申请号：US18328991

申请日：2023-06-05

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M. Beaven ,  Craig W. Bemment ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Martin K. Yates

IPC: F02C9/40 ,  F02C9/28

Abstract: The present application provides a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US11149690B2

公开(公告)日：2021-10-19

申请号：US16106813

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Nigel H S Smith ,  Marco Barale ,  Kashmir S. Johal ,  Stephane M M Baralon ,  Craig W. Bemment

IPC: F02K3/06 ,  F02C7/04 ,  F02C7/36 ,  F02C3/06 ,  F01D5/14 ,  F01D5/16

Abstract: A gas turbine engine 10 is provided in a fan root to tip pressure ratio, defined as the ratio of the mean total pressure of the flow at the fan exit that subsequently flows through the engine core (P102) to the mean total pressure of the flow at the fan exit that subsequently flows through the bypass duct (P104), is no greater than a certain value. The gas turbine engine 10 may provide improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

公开(公告)号：US20250012223A1

公开(公告)日：2025-01-09

申请号：US18888979

申请日：2024-09-18

Applicant: Rolls-Royce plc

Inventor： Peter SWANN ,  Christopher P. Madden ,  Craig W. Bemment

IPC: F02C9/40 ,  F02C9/28 ,  F23R3/34

Abstract: A gas turbine engine includes a staged combustion system having pilot fuel injectors and main fuel injectors. A fuel delivery regulator controls delivery of fuel to the pilot and main fuel injectors, receives fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a second fuel characteristic. In a transition range of operation between the pilot-only and the pilot-and-main ranges of operation, fuel is delivered to both the pilot and main fuel injectors at a transition staging ratio different from the pilot-and-main staging ratio. The fuel delivery regulator delivers fuel to one or both the pilot and main fuel injectors during the transition range of operation having a different fuel characteristic from fuel delivered to one or both the pilot and main fuel injectors during at least part of the pilot-and-main range of operation.

公开(公告)号：US11078838B2

公开(公告)日：2021-08-03

申请号：US16396918

申请日：2019-04-29

Applicant: ROLLS-ROYCE plc

Inventor： Craig W. Bemment ,  David P. Scothern

IPC: F02C6/08 ,  B64D13/06 ,  F02C9/18 ,  F02C7/277 ,  F02C7/32 ,  F02C7/36

Abstract: A method of operating a gas turbine engine compressor. The engine comprises a compressor having an environmental control system bleed port having an outlet in fluid communication with an aircraft environmental control system air duct, and an air turbine starter configured to rotate a compressor shaft of the gas turbine engine. The air turbine starter has an inlet in fluid communication with the environmental control system air duct via an air turbine valve. The method comprises determining a surge margin of the compressor, and where the surge margin of the compressor is determined to be below a predetermined minimum surge margin, opening the air turbine valve to supply air to the air turbine.

公开(公告)号：US20250003370A1

公开(公告)日：2025-01-02

申请号：US18884969

申请日：2024-09-13

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P. MADDEN ,  Craig W. Bemment ,  Andrew T Smith ,  Peter Swann

IPC: F02C7/264 ,  B64D27/10 ,  F23R3/28

Abstract: A gas turbine engine has a combustor with a combustion chamber and a plurality of fuel spray nozzles including a first subset of nozzles and a second subset of nozzles. The first subset of nozzles are supplied with more fuel than the second subset of nozzles. A ratio of the number of nozzles in the first subset to the number of nozzles in the second subset is in the range of 1:2 to 1:5. A method includes providing fuel to the one or more fuel-oil heat exchangers, transferring heat from oil to the fuel, and providing the fuel from the one or more fuel-oil heat exchangers to the fuel spray nozzles. Heat is transferred from the oil to the fuel to lower a viscosity of the fuel to 0.58 mm2/s or lower on injection of the fuel into the combustion chamber at cruise conditions.

公开(公告)号：US20240384689A1

公开(公告)日：2024-11-21

申请号：US18785965

申请日：2024-07-26

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Christopher P. Madden ,  Craig W. Bemment

IPC: F02C9/40 ,  F02C9/28

Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

公开(公告)号：US11085399B2

公开(公告)日：2021-08-10

申请号：US16106853

申请日：2018-08-21

Applicant: ROLLS-ROYCE plc

Inventor： Benedict R. Phelps ,  Mark J. Wilson ,  Gabriel Gonzalez-Gutierrez ,  Nigel H S Smith ,  Marco Barale ,  Kashmir S. Johal ,  Stephane M M Baralon ,  Craig W. Bemment

IPC: F02K3/06 ,  F02C7/04 ,  F01D5/14 ,  F02C3/06

Abstract: A gas turbine engine 10 is provided in which a fan having fan blades in which the camber distribution along the span allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.