Pratt-Whitney Canada Corp

Pratt & Whitney Aircraft of Canada Ltd.

Parthasarathy Sampath

Honza Stastny

Bhawan Bhai Patel

John Greer

Lev Alexander Prociw

Eduardo David Hawie

Jason Araan Fish

Richard Alan Kostka

Kenneth D Parkman

Jeffrey Richard Verhiel

Stephen Phillips

Yvan Schraenen

Russell Parker

Carol Desjardins

Oleg Morenko

Kian McCaldon

Harris Shafique

Nigel Caldwell Davenport

Lorin Markarian

Denis Leclair

Maurice Weinberg

Jian-Ming Zhou

Bhawan Bhal Patel

Andre Chevrefils

Qing-Ping Zheng

Robert Desroches

Robert Ming Aze

John A Saintsbury

A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides, providing cold side details separately from the base sheet, and mounting the cold side details to the cold facing side of the base sheet. The cold side details may be brazed to the base sheet.

Method for a fabricated heat shield with rails and studs mounted on the cold side of a combustor heat shield

A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body.

Fuel nozzle and method of repair

A combustor with a liner where each of the walls has a respective circumferential row of dilution holes defined therethrough adjacent a junction between the primary zone and the dilution zone. In the primary zone, the inner surface of each of the walls is covered by at least one heat shield attached thereto and spaced apart therefrom to allow air circulation between the inner surface and the at least one heat shield, the walls each having a plurality of cooling holes defined therethrough having a smaller diameter than that of the dilution holes. In the dilution zone, the inner surface of each of the walls is free of heat shields, and the walls each have a plurality of effusion cooling holes defined therethrough and having a smaller diameter than that of the dilution holes.

Combustor for gas turbine engine

A method of repairing a modular gas turbine fuel nozzle tip, having a fuel-conveying body and an annular cap fastened to the body by at least two fasteners, includes removing the fasteners, replacing the annular cap with a replacement annular cap, and interconnecting the replacement annular cap and the body using new fasteners.

A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.

Method for manufacturing a combustor heat shield

A gas turbine combustor is provided with a dome heat shield having a fuel nozzle opening, the opening receiving a floating collar assembly for permitting relative movement between nozzle and heat shield. The floating collar is provided with a louver to provide film cooling to the face of the combustor heat shield and, thus, improve cooling thereof.

Combustor floating collar with louver

Combustor heat shield

A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.

Gas turbine engine combustor with improved cooling

A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.

A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Combustor liner v-band design

A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.

Combustor having means for directing air into the combustion chamber in a spiral pattern

A gas turbine fuel nozzle head includes an outlet passage having a curved annular transitional surface extending smoothly to a substantially radial and annular surface relative to a central axis of the fuel nozzle head, for providing a low cost and compact structure with improved cold start and altitude re-light capabilities.

Fuel injector head

Combustor liner V-band design

A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor. A fuel gallery extends through the fuel injector tip and defines an annular fuel nozzle radially within the first air passages, whereby the first air passages are arranged to atomize the fuel emanating from the annular fuel nozzle, and second fuel passages are arranged in annular array in the injector tip spaced radially outwardly from the first air passages whereby the second passages are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.

Growing community of inventors

Mississauga, Canada

Parthasarathy Sampath