1
Edward Claude Rice, Robert Anthony Ress Jr, Timothy Carl Roesler: Interchangeable combustor chute. Allison Advanced Development Company, Rolls Royce Corporation, Woodard Emhardt Naughton Moriarty & McNett, March 5, 2002: US06351949 (36 worldwide citation)

An interchangeable combustor chute for directing airflow into a gas turbine engine combustor. In one aspect the combustor chute is secured to the combustor liner by mechanical fastener. The combustor chute is formed of a high temperature resistant material such as ceramics.


2
David Levi Sutterfield, Von David Baker, Jagdish Singh Sokhey: Thrust vectoring mechanism. Rolls Royce Corporation, Allison Advanced Development Company, Woodard Emhardt Naughton Moriarty & McNett, May 7, 2002: US06382559 (35 worldwide citation)

A thrust vectoring mechanism to vector thrust and control discharge throat area includes four or more vanes mounted across the outlet of a nozzle in a cascade arrangement. The mechanism further includes a rod to control pivoting of each of the vanes that may be selectively rotated with one or more a ...


3
Philip H Snyder: Particle separator for a turbine engine. Rolls Royce Corporation, Barnes & Thornburg, March 2, 2004: US06698180 (35 worldwide citation)

A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbin ...


4
Lawrence Evans Brown, Timothy Paul Fuesting, Joseph Jefferson Beaman Jr, Suman Das: Method and apparatus for making components by direct laser processing. Rolls Royce Corporation, Board of Regents The University of Texas, Woodard Emhardt Naughton Moriarty & McNett, March 12, 2002: US06355086 (34 worldwide citation)

The present invention relates to a method an apparatus for fabricating a component by a direct laser process. One form of the present invention contemplates a gas turbine engine blade having an abrasive tip formed directly thereon.


5
Steven Arlen Klusman, Mark Stephen Henry: Self contained squeeze film damping system. Rolls Royce Corporation, Krieg DeVault, February 12, 2008: US07329048 (26 worldwide citation)

A fluid damping system for damping a shaft within a gas turbine engine component. The fluid damping system including a damping liquid and a pressurized gas in a closed self contained system. In one aspect the damping liquid is cooled by being disposed in a heat transfer relationship with a fuel.


6
David Mark Rogers: Overspeed detection techniques for gas turbine engine. Rolls Royce Corporation, Woodard Emhardt Naughton Moriarty & McNett, November 27, 2001: US06321525 (25 worldwide citation)

Unique systems and methods are disclosed to detect and remediate an overspeed condition of a gas turbine engine. Such techniques include sensing rotational speed of a rotating member of a gas turbine engine and providing a first speed threshold that varies with rotational acceleration of this member ...


7
Richard Patrick Chesnes, Raymond Ruiwen Xu: Nickel diffusion braze alloy and method for repair of superalloys. Rolls Royce Corporation, Woodard Emhardt Naughton Moriarty & McNett, September 24, 2002: US06454885 (25 worldwide citation)

A braze alloy powder mixture that includes a low-melt powder composition and a high-melt powder composition. The low-melt powder composition is made of one or more low-melt powders and includes 50-70% Ni, 8-20% Cr, 8-15% Ta, 4-10% Co, 2-7% Al, and up to 2.25% B. The high-melt powder composition is m ...


8
Philip H Snyder: Particle separator for a gas turbine engine. Rolls Royce Corporation, Barnes & Thornburg, December 31, 2002: US06499285 (25 worldwide citation)

A particle separator for a gas turbine engine includes a housing defining an annular first flow passage, an annular first opening, and an annular second flow passage positioned in fluid communication with the first flow passage through the first opening. The particle separator also includes a plural ...


9
Philip Harold Snyder: Pulsed detonation engine wave rotor. Rolls Royce Corporation, Woodard Emhardt Naughton Moriarty & McNett, September 17, 2002: US06449939 (24 worldwide citation)

A pulsed detonation engine wave rotor apparatus and method of using a pressure wave to compress a buffer gas disposed within the engine flow passages. The high pressure buffer gas is routed out of the wave rotor and subsequently reintroduced to the wave rotor to discharge and scavenge the latter sta ...


10
Jushan Chin, Nader K Rizk, Mohan K Razdan, Andre W Marshall: Fuel premixing module for gas turbine engine combustor. Rolls Royce Corporation, Krieg Devault, November 29, 2005: US06968692 (22 worldwide citation)

A fuel-air premixing module is designed to reduce emissions from a gas turbine engine. In one form, the premixing module includes a central pilot premixer module with a main premixer module positioned thereround. Each of the portions of the fuel-air premixing module include an axial inflow swirler w ...