United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Jeffrey Jay Lienau

Robert Newman

Anthony P Cherolis

Conway Chuong

Joshua Daniel Winn

Jonathan Lemoine

Dustin Wayne Davis

Paul K Sanchez

Kevin Zacchera

Fumitaka Ichihashi

Rajendra Prasad Uppara Allabanda

Timothy S Snyder

Steven D Porter

James B Hoke

Gregory E Reinhardt

Scott D Lewis

John S Tu

John T Ols

Seth A Max

John H Mosley

Kristin Kopp-Vaughan

William J Yeager

Cheng-Zhang Wang

Baris A Sen

Krishna Nelanti

Senthil Prasad Mathiyalagan

Venu Sambarapu

Prabaharan Manoharan

A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The combustor further includes a liner panel mounted to one of the inner shell and the outer shell aft of the bulkhead. The liner panel includes a first section including a first plurality of effusion holes. A first portion of the first plurality of effusion holes extends in a substantially circumferential direction. A second portion of the first plurality of effusion holes, disposed forward of the first portion, transitions from the substantially circumferential direction toward a substantially forward direction. A third portion of the first plurality of effusion holes, disposed aft of the first portion, transitions from the substantially circumferential direction to a substantially aft direction.

Convection cooling at low effusion density region of combustor panel

Flow diverters for installation in mid-turbine frame systems at a conduit outlet of gas turbine engines are described. The flow diverters include a diverter body having a connector portion defining a diverter inlet, a diverter extension at least partially defining a diverter outlet, and a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90&#xb0; from the first direction as the flow passes from the diverter inlet to the diverter outlet.

Flow diverter for mid-turbine frame cooling air delivery

An air seal assembly for a gas turbine includes a flow path platform. The air seal assembly further includes a casing disposed radially outside the flow path platform. The air seal assembly further includes an annular finger seal mounted to the casing and disposed between the flow path platform and the casing. The annular finger seal includes a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform. The third circumferential portion includes a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform.

Air seal assembly

A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

Combustor heat shield and method of cooling same

A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

Mid turbine frame including a sealed torque box

A combustor panel may comprise a dilution hole, a plurality of film cooling holes each of the plurality comprising an inlet and an outlet, a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, wherein each of film cooling holes of the first group have a first outlet angle oriented radially toward the center of the dilution hole, and a second group of the plurality of film cooling holes arranged radially outward of the first group and relatively circumferentially between the first group.

Dilution/effusion hole pattern for thick combustor panels

A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

Cooling passages for a mid-turbine frame

A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. The mid-turbine frame also includes multiple spokes protruding radially outward from the inner frame case. The mid-turbine frame also includes at least one service line connected to the inner frame case.

An air seal for a gas turbine engine platform comprises a flow path platform, a seal retention ring, a finger seal. The seal retention ring is situated radially adjacent the flow path platform. The finger seal is retained by the seal retention ring between the flow path platform and the seal retention ring. The finger seal comprises a first ply with first keyhole slots, a second ply with second keyhole slots circumferentially offset relative to the first keyhole slots, and a foil layer. The foil layer is disposed between the first and second plies. The finger seal has a series of cooling holes in the outer circumferential segment to cool the outer diameter of the seal. In addition, leakage between the finger seal and the flow path platform cools the inner diameter of the seal.

Cooled finger seal

A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

Seal support structures for turbomachines

A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.

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Wethersfield, CT, United States of America

Jeffrey Jay Lienau