United Technologies Corporation

Raytheon Technologies Corporation

Paul W Palmer

Glenn Levasseur

Robert Russell Mayer

George J Kramer

John J Korzendorfer

Peter Balawajder

Mahamoud Coulibaly

Nicholas Lefevre

Paul J Colucci

Jonathan Lemoine

Mark Borja

Nicholas W Kantany

Jonathan P Burt

David T Feindel

David C Pimenta

Fernando K Grant

Andrew S Miller

Anders Carl Olson

Peter Staffier

Adeyemi E Alade

Eric Baker

Shu Liu

Raymond N Frick

Anders C Olson

Stephanie Ernst

Igor S Garcia

A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.

Load transfer in turbine exhaust case

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 seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.

Duct blocker seal assembly for a gas turbine engine

A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.

Gas turbine engine blade outer air seal thermal control system

A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.

Blade tip clearance systems

A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.

An assembly for use with a gas turbine engine includes a tie rod and a connector. The tie rod, which is for extending radially outwardly from a latitudinal axis of the gas turbine engine, has a hollow length having a longitudinal axis and a base having a width in parallel to the latitudinal axis. The base has a counterbore disposed therein and is wider than a width of the length. The connector, for attaching the base of the tie rod to a bearing assembly of the gas turbine engine, has a hollow body having a shaft removably attaching, at a first end portion thereof, to the counterbore. The shaft and the counterbore are disposed in parallel with the longitudinal axis.

Gas turbine engine tie rod retainer

A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.

Gas turbine engine seal carrier

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 gas turbine engine includes bound assemblies with an inner diameter ring, struts, and an outer diameter ring. The strut is connected to the inner diameter ring and extends radially outward therefrom to connect to the outer diameter ring. A strain relief feature is disposed adjacent to or at the connection between the strut and the inner diameter ring and/or the outer diameter ring. The strain relief feature lengthens the arc segment of fillet curvature. For a constant thermal punch load, the lengthened arc segment of fillet curvature results in a decreased maximum strain in the bound assembly.

Strain tolerant bound structure for a gas turbine engine

The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative movement between the plurality of scoops and the mixer element while the fixed brackets provide only attachment between the mixer element and the plurality of scoops. The first sliding bracket includes a first flange that is fixedly mounted to the mixer element and a second flange that is biased against a surface of the scoop. A second sliding bracket is fixedly mounted to the mixer element and adjustably mounted to the scoop. The second sliding bracket includes an attachment hole and the scoop includes an adjustment slot. A fastener assembly including a spacer is received within the adjustment hole and the adjustment slot to allow relative movement between the mixer element and the scoop.

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South Glastonbury, CT, United States of America

Paul W Palmer