Pratt-Whitney Canada Corp

Honza Stastny

Robert Sze

Parthasarathy Sampath

Jeffrey Richard Verhiel

Bhawan Bhai Patel

John Greer

Kian McCaldon

Eduardo David Hawie

Sri Sreekanth

Kenneth D Parkman

Tin Cheung John Hu

Stephen Phillips

Yvan Schraenen

Carol Desjardins

Lev Alexander Prociw

Oleg Morenko

Aleksandar Kojovic

Jian-Ming Zhou

Jakub Strzepek

Ram Kulathu

Dan Titirica

Sudhakara Reddy Annem

Balakrishna Gaja

Bharath Mandya Nagaraj

Eng Lim

There is disclosed a double skin combustor for a gas turbine engine. The combustor has a radially inner liner and a radially outer liner defining therebetween an annular combustion chamber. The radially inner liner and the radially outer liners both have a hot skin and a cold skin defining a cooling cavity therebetween. The cold skin has a plurality of segments joined to one another by sliding joints. The cooling cavity between the hot skin and the cold skin may be compartmentalized into individual cavities between the sliding joints.

Double skin combustor

The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.

Small exit duct for a reverse flow combustor with integrated fastening elements

The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.

Combustor heat shield with carbon avoidance feature

A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct.

Combustor sliding joint

The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.

Small exit duct for a reverse flow combustor with integrated cooling elements

A floating collar assembly for a gas turbine engine combustor includes a ferrule having a peripheral wall and a recessed surface bounded by the peripheral wall, the recessed surface of the ferrule including a particulate collecting groove adjacent the peripheral wall, and a cap secured to the peripheral wall of the ferrule. The recessed surface of the ferrule, an interior surface of the cap and the peripheral wall of the ferrule define a cavity. A floating collar is disposed within the cavity and includes a peripheral flange inwardly spaced a distance from the peripheral wall of the ferrule.

Particulate buildup prevention in ignitor and fuel nozzle bosses

A gas turbine engine comprising a combustor having a combustor liner assembly and a mounting bracket provided on the combustor liner assembly, a floating collar being slidingly received on the mounting bracket for relative sliding movement in a plane normal to an axis of an igniter opening in the liner assembly. The floating collar includes an annular surface defining a collar opening, and an igniter having an axis concentric with the axis of the collar opening is sealingly engages the annular surface. A plurality of purge openings defined in at least one of the igniter and the floating collar form cooling airflow passages communicating from the plenum to the cavity.

Combustor igniter assembly

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 gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.

Combustor floating collar assembly

A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.

Combustor skin assembly for gas turbine engine

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 heat shield unit for a gas turbine engine combustor comprises a panel body secured to a combustor liner. A first surface of the body is oriented toward a combustion zone of a combustor. A second surface is oriented toward the liner. The body is separated into upstream and downstream portions. Pin fins project from the second surface of the body. The pin fins are arranged in arrays of at least two different densities of volume of pin fins per unit volume. One density, lower than the second density, is in the upstream portion and another in the downstream portion of the body. Connectors connect the body to the liner with a line between the upstream and downstream portions of the body aligned with fluid-coolant injection apertures in the liner. A gas turbine engine combustor and a method for cooling a heat shield unit in a combustor liner of a gas turbine engine are also provided.

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Georgetown, Canada

Honza Stastny