公开(公告)号：US09683909B2

公开(公告)日：2017-06-20

申请号：US14665792

申请日：2015-03-23

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Sermed Sadig ,  Jochen Rupp

IPC: G01L7/00 ,  G01L19/06 ,  G01M15/14

CPC classification number: G01L19/0609 ,  G01M15/14

Abstract: The present invention relates to a pressure-measuring device for measuring dynamic pressures in the high-temperature range, with a pressure line connected to a volume subjected to pressure and with a pressure sensor which is arranged at a distance from the inlet area of the pressure line to the volume, wherein the pressure line is provided with at least one pinhole diaphragm and connected to an additional damping volume, as well as to the use of the pressure-measuring device in a combustion chamber of a gas turbine.

公开(公告)号：US10704517B2

公开(公告)日：2020-07-07

申请号：US15837446

申请日：2017-12-11

Applicant: ROLLS-ROYCE plc

Inventor： David P. Wilson ,  John E. Rimmer ,  Jochen Rupp ,  Damian Martin ,  Emmanuel V. Aurifeille ,  Kyriakoulis L. Resvanis ,  Michael J. Allitt

IPC: F02M61/14 ,  F23R3/28 ,  F23R3/00 ,  F23R3/50

Abstract: A combustion chamber comprising an upstream end wall, at least one annular wall, at least one fuel injector and at least one seal. The at least one annular wall being secured to the upstream end wall. The upstream end wall having at least one aperture. Each fuel injector being arranged in a corresponding one of the apertures in the upstream end wall and each seal being arranged in a corresponding one of the apertures in the upstream end wall and around the corresponding one of the fuel injectors. Each seal having an inner surface facing the corresponding one of the fuel injectors and an outer surface facing away from the corresponding one of the fuel injectors. Each seal abutting the corresponding one of the fuel injectors. The downstream end of each seal increasing in diameter in a downstream direction and the upstream end of each seal having a radially extending flange. Each seal having a plurality of coolant apertures extending axially through the radially extending flange and/or each seal having a plurality of thermal conductors extending axially from the radially extending flange to the downstream end of the seal.

公开(公告)号：US10533746B2

公开(公告)日：2020-01-14

申请号：US15359472

申请日：2016-11-22

Applicant: ROLLS-ROYCE plc

Inventor： John E Rimmer ,  Michael A Macquisten ,  Stephen J Mills ,  Jochen Rupp ,  Lynn I Steward ,  Murthy V Ravikanti

IPC: F02C1/00 ,  F23R3/00 ,  F02C7/12

Abstract: A gas turbine engine combustion chamber arrangement includes an annular outer wall and annular inner wall including an upstream and a downstream row of tiles. The downstream end of each tile in the upstream row of tiles has a rail extending towards and sealing with the outer wall and a lip extending in a downstream direction towards the tiles in the downstream row of tiles. The outer wall has a row of apertures to direct coolant onto the lips of the tiles in the upstream row of tiles. The downstream end of each tile in the upstream row of tiles has a plurality of fences extending in a downstream direction from the rail and each fence extends from the outer surface of the lip towards the outer wall. The row of apertures in the annular outer wall is arranged to direct coolant onto the lip between two circumferentially adjacent fences.

公开(公告)号：US11041626B2

公开(公告)日：2021-06-22

申请号：US15457456

申请日：2017-03-13

Applicant: ROLLS-ROYCE plc

Inventor： Hua Wei Huang ,  Jochen Rupp ,  Michael Whiteman

IPC: F23R3/00 ,  F23R3/34 ,  F02C9/28 ,  F02C9/32 ,  F23N1/00 ,  F02C9/26 ,  F23R3/50

Abstract: A combustion chamber system has pilot and main fuel manifolds, and pilot and main fuel nozzles. Each pilot nozzle is connected to the pilot manifold. Each main nozzle is connected to the main manifold. A greater total amount of fuel is supplied to the pilot nozzles than to the main nozzles. A greater amount of fuel is supplied to pilot nozzles at, or in, a first region of the combustion chamber than to pilot fuel nozzles at, or in, a second region. A greater amount of fuel is supplied to the main nozzles at, or in, the first region than to the main nozzles at, or in, the second to improve combustion efficiency, weak extinction and relight of the combustion chamber in a first mode of operation. A greater total amount of fuel is supplied to the main nozzles than to the pilot nozzles in a second mode of operation.

公开(公告)号：US09169804B2

公开(公告)日：2015-10-27

申请号：US14314821

申请日：2014-06-25

Applicant: ROLLS-ROYCE PLC

Inventor： Jochen Rupp ,  Anthony John Moran

IPC: F02K1/00 ,  F02K1/34 ,  F23R3/00

CPC classification number: F02K1/34 ,  F23R3/002 ,  F23R2900/00014

Abstract: A duct and a method for damping pressure waves caused by thermoacoustic instability, the duct comprising: a locking Helmholtz resonator positioned on the circumference of the duct, the locking Helmholtz resonator tuned to a first frequency; and one or more damping Helmholtz resonators positioned on the circumference of the duct at or adjacent to 90 and/or 270 degrees from the locking Helmholtz resonator, wherein the damping Helmholtz resonators are tuned to a second frequency which is different from the first frequency of the locking Helmholtz resonator.

Abstract translation: 一种用于阻止由热声不稳定引起的压力波的管道和方法，所述管道包括：位于所述管道的圆周上的锁定亥姆霍兹共振器，所述锁定亥姆霍兹共振器被调谐到第一频率; 以及一个或多个阻尼亥姆霍兹谐振器，其位于与锁定亥姆霍兹共振器90°和/或270度处或相邻的管道的圆周上，其中阻尼亥姆霍兹共振器被调谐到与第一频率不同的第二频率 锁定亥姆霍兹共振器。