United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Alexander Broulidakis

Matthew A Devore

Christopher Treat

Anthony P Cherolis

Joseph James Sedor

Joshua Daniel Winn

Jonathan Lemoine

Paul K Sanchez

William P Stillman

Michael A Disori

Patrick Michael Nadeau

Matthew Andrew Hough

Alexander W Williams

Kevin Zacchera

Andreas Sadil

Dave J Hyland

Andrew D Burdick

Alberto A Mateo

Kalpendu J Parekh

Christopher B Lyons

Jeremy Styborski

Jonathan M Jause

Peter E Gunderson

David J Hyland

Steven W Trinks

David Donald Chapdelaine

Adam J Diener

Patrick M Devaney

Michael D Collier

Patrick M Nadeau

Jr Dominic J Mongillo

Alberto Mateo

Jeremy Styborksi

In a featured embodiment, a heat exchanger includes a plate including a plate portion having outer walls. A plurality of internal passages extend between end portions. A ratio between an outer wall cross-sectional thickness at one of the end portions and a cross-sectional wall thickness of the outer wall within the plate portion is greater than 2.5 and no more than 10. An inlet manifold is attached to the inlet end. An outlet manifold is attached to the outlet end.

Cast plate heat exchanger with tapered walls

A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

Mid-turbine frame assembly

A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.

Shaped leading edge of cast plate fin heat exchanger

A gas turbine engine component has an engine case structure surrounding an engine center axis. A plurality of holes are formed in the engine case structure, wherein the holes are circumferentially spaced apart from each other about the engine center axis. The plurality of holes includes at least one balance hole and at least one service hole that is configured to allow another engine component to pass through the at least one service hole. At least one cover is configured to cover at least one balance hole such that air is prevented from passing through the at least one balance hole.

Gas turbine engine case flow blocking covers

A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor section. The combustor includes a combustor region defined by at least one bulkhead panel and at least one heat shielding panel inside the combustor region. The at least one heat shielding panel is connected to the bulkhead panel via at least one cooled fastener.

Attachment scheme for a ceramic bulkhead panel

A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.

A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.

Mid-turbine frame assembly for a gas turbine engine

A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.

Hybrid diffuser case for a gas turbine engine combustor

Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.

Shim to maintain gap during engine assembly

A fastener assembly includes a first component including a first fastener opening that has a cylindrical portion and a conical portion. A second component includes a second fastener opening. A fastener for extending through the first fastener opening and the second fastener opening and a clinch nut for attaching to the fastener is included.

Clinch nut bolt hole geometry

A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion. At least one gusset extends between the cylindrical portion and the flange. At least one gusset extends to a perimeter of the flange.

Cooling passages for a mid-turbine frame

A mid-turbine frame is provided. The mid-turbine frame may comprise an inner case having an annular surface with an interface section disposed on the annular surface. The interface section may include an interface feature. A balancing section may be disposed on the annular surface defining an opening and disposed circumferentially adjacent the interface section.

Growing community of inventors

Tolland, CT, United States of America

Alexander Broulidakis