United Technologies Corporation

Other

Raytheon Technologies Corporation

George J Kramer

Robert Russell Mayer

Paul W Palmer

Paul A Smith, Jr

Jeffrey S Smith

Gary D Roberge

Stephen Karl Kramer

Donald William Peters

Gary A Schirtzinger

Thomas M Barry

Charles R Jones

Kenneth W Froemming

Arthur Cordes

A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

Gas turbine engine mid turbine frame bearing support

A fan section to be incorporated into a gas turbine engine has a rotor and a plurality of fan blades. The fan blades deliver air into a bypass duct defined inwardly of the nacelle and into a core engine. There are static vanes inward of the nacelle. A surface of the fan section is provided with a removable film material. A gas turbine engine and a method of refurbishing a surface are also disclosed.

Removable film for airfoil surfaces

An exhaust nozzle for a gas turbine engine includes a gas path liner connected to an interior surface of an exhaust nozzle flap. The gas path liner includes a liner backbone that extends along a liner axis, and a plurality of liner panels sequentially connected to the liner backbone along the axis. Each liner panel includes a panel length that extends axially from a first panel end to a second panel end, where the panel length thermally expands independent of the liner backbone

Gas path liner for a gas turbine engine

A liner portion has an exhaust liner portion with an inner face extending to an outward extending flange. Cooling grooves formed in the flange have a radially outward inlet point and a radially inner outlet point. A flow area at the inlet point is smaller than the flow area at the outlet point.

Exhaust liner flange cooling

An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly.

Seal assembly for liners of exhaust nozzle

The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment.

Stationary non-rotating brush seals

An attachment structure and ceramic matrix composite liner combination for a gas turbine engine has a ceramic matrix composite liner including plural flanges extending away from a face of said liner. The flanges have an opening and a bracket secured to the flanges by a securement member extending through the opening in the flange, and through an opening in the bracket. The flanges are secured to the securement member through at least one washer having a spherical face facing a spherical recess in the flanges.

Ceramic matrix composite liner attachment

A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a disk and a rod. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The disk is slidably engaged with the bracket. The rod is for connecting to an exhaust duct of the gas turbine engine. The rod is pivotably connected to the disk.

Pivoting ball stop for exhaust duct liner hanger

A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a washer, a rod and a cap. The bracket is for connection to an exhaust duct liner of a gas turbine exhaust system. The washer is connected to the bracket at a slip joint. The rod is connected to the washer at a ball joint. The cap for is for connecting to an exhaust duct of the gas turbine exhaust system. The cap is connected to the rod.

Spherical button washer for exhaust duct liner hanger

A liner and attachment structure has an exhaust liner for use in a gas turbine engine. At least one hanger has feet secured to the liner. The hanger has an aperture extending at a central web. A flanged washer is received within the opening in the hanger. The flanged washer allows adjustment relative to the hanger. The flanged washer has a spherical recess. A collet has a plurality of part-spherical fingers separated by slots, and are received in the spherical recess of the flanged washer. A member extends into the collet to hold the part-spherical fingers radially outwardly. The member is also utilized to secure static structure, and to secure the liner to the static structure.

Spherical collet for mounting a gas turbine engine liner

A liner assembly for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A hanger assembly supports the liner relative to the duct. The hanger assembly includes a body segment attached to the liner and first and second washers defining a gap therebetween that receives a portion of the body segment. The gap between the washers and the body segment provides for relative movement caused by differences in thermal growth within the liner. An attachment member extending between the body section and the duct includes spherical ends that are seated on the first and second washers to accommodate misalignments during assembly.

Liner hanger with spherical washers

A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.

A seal for a duct having an upstream portion and a downstream portion, the duct upstream portion and the duct downstream portion separated by a first gap, includes a first portion having a length greater than a width of the first gap between the first portion and the second portion, the first portion having a first thickness, a first upstream end and a first downstream end; a second portion having a length greater than a width of the gap between the first portion and the second portion, the second portion having a second thickness, a second upstream end and a second downstream end; and an attachment between the first portion and the second portion such that the first portion and the second portion move relative to each other, wherein the first portion is inside the duct and the second portion is outside of the duct.

Clamshell seal

A thermally insulative component is a thermal barrier panel attached to a rigid structural member with means for attaching the insulative component to an external structure. The connection between the structural member and the thermal barrier panel is mechanically compliant to minimize intercomponent stress build up during operation. The thermal barrier panel is a fiber wrapped ceramic oxide foam insulating structure.

Thermally insulative attachment

A thermal relief slot is formed by including a lateral slot in each of three overlying sheet metal sheets with the upper and lower slots being in overlying position and the middle slot being axially spaced therefrom and the three sheets being bonded into an integral sheet metal sheet assembly except for the area extending over the relief slots. The edge of the upper and/or lower outer edges of adjacent the relief slots may be chamfered to prevent fraying of the edges. A two sheet assembly includes the relief slots axially spaced and two sheet metal sheets are bonded except for the area including and extending between the two relief slots.

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Tolland, CT, United States of America

George J Kramer