公开(公告)号：US10907831B2

公开(公告)日：2021-02-02

申请号：US15972320

申请日：2018-05-07

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： Jack D. Petty, Sr. ,  John Holdcraft ,  Kevin Sauer

IPC: F23R3/14 ,  F23R3/28 ,  F23D11/10 ,  F23R3/26

Abstract: A fuel injection system may include a fuel spray nozzle including a nozzle head and a nozzle stem. The nozzle head may include an air channel and a swirler in fluid communication with the air channel. The nozzle stem may extend into a compressor discharge pressure cavity and convey fuel to the air channel. The air channel may combine air from the swirler with the fuel from the nozzle stem and convey a mixture of fuel and air to a combustor. The fuel injection system may further include a scoop. The scoop may be coupled to the fuel spray nozzle. The scoop may receive air that flows into the compressor discharge pressure cavity from a diffusor. An outer surface of the fuel spray nozzle and an inner surface of the scoop define a duct in fluid communication with the swirler. The swirler may receive air from the duct.

公开(公告)号：US11015812B2

公开(公告)日：2021-05-25

申请号：US15972309

申请日：2018-05-07

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Jack D. Petty, Sr. ,  John D. Holdcraft ,  Kevin M. Sauer ,  Duane A. Smith

IPC: F23R3/60 ,  F23R3/50 ,  F23R3/00 ,  F23R3/06 ,  F23M5/04

Abstract: A combustor liner assembly is provided including an inlet wall, an inner wall, an outer wall, and a plurality of fasteners. The inlet wall has an opening into a combustion chamber. The inner wall is coupled to the inlet wall at a first end of the combustor liner. The inner wall defines a radially inner end of the combustion chamber. The outer wall includes a plurality of segments. The plurality of segments define a radially outer end of the combustion chamber. A first portion of the plurality of fasteners couples each of the plurality of segments to another of the plurality of segments. A second portion of the plurality of fasteners couples at least one of the plurality of segments to the inlet wall at the first end of the combustor liner.

公开(公告)号：US10974840B2

公开(公告)日：2021-04-13

申请号：US16668345

申请日：2019-10-30

Applicant: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.

Inventor： Jack D. Petty, Sr. ,  Colin Faucett ,  Kenneth M Pesyna ,  James C. Loebig

IPC: B64D33/04 ,  F02K1/82 ,  F02C3/04 ,  F02C7/24 ,  B64D27/12 ,  F01D25/30 ,  F01D9/02

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

公开(公告)号：US10451276B2

公开(公告)日：2019-10-22

申请号：US14137267

申请日：2013-12-20

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Jack D. Petty, Sr. ,  Mohan Razdan ,  Michael S. Bell ,  Michel S. Smallwood ,  Tab M. Heffernan

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/60

Abstract: A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures.

公开(公告)号：US10087852B2

公开(公告)日：2018-10-02

申请号：US14577064

申请日：2014-12-19

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Andrew J. Eifert ,  Oran Watts ,  Jack D. Petty, Sr.

IPC: F02C9/28 ,  F02C7/232 ,  F02C7/236 ,  F02C7/228 ,  F02C9/26

Abstract: A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps. The first and second fuel pumps are downstream from the fuel splitter. The first fuel nozzle is fluidly coupled to the first fuel pump by a first fuel stream. The second fuel nozzle is fluidly coupled to the second fuel pump by a second fuel stream. The common drive is configured to drive the first and second fuel pumps at a same speed. The controller system is configured to determine a first fuel pressure in the first fuel stream, determine a second fuel pressure in the second fuel stream, and identify a difference between the first and second fuel pressures.