United Technologies Corporation

Christopher R Joe

Paul M Lutjen

Dominic J Mongillo, Jr

Eric A Hudson

Gary L Grogg

Friedrich O Soechting

Keith A Santeler

William S Kvasnak

Ronald S LaFleur

Douglas A Hayes

Joe Moroso

Daniel A Ward

Frank J Cunha

Blake J Luczak

James N Knapp

Eric L Couch

John D Wiedemer

Eric P Letizia

Scott W Gayman

Karen A Thole

Michael F Benamati

Jr Dominic J Mongillo

A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating.

Blade outer air seal having partial coating

An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.

Turbine blade tip clearance control

An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising.

An example turbine component cooling arrangement includes a film plate having a plurality of film channels extending from film channel entrances on a first side of the film plate to corresponding film channel exits on an opposing second side of the film plate. The arrangement also includes an impingement plate establishing a plurality of impingement channels. The impingement plate is spaced a distance from the film plate. The plurality of impingement channels are configured to direct a fluid across the distance to contact the film plate between adjacent ones of the film channel entrances. In one example, the distance from the film plate to the impingement plate is between two and four times more than diameter of one of the impingement channels.

Cooling arrangement for a turbine engine component

A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating.

A blade outer air seal for a gas turbine engine has a plurality of stacked panels extending for at least a part circumferential extent, and extending from a radially outer location to a radially inner location. The plurality of stacked panels are mounted together. A turbine section is also claimed.

Blade outer air seal formed of stacked panels

A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.

Filter system for blade outer air seal

A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid.

Heat transfer augmentation in a compact heat exchanger pedestal array

A turbine outer air seal includes, in a radially inner major surface thereof, at least one circumferential groove accommodating a plurality of holes which supply air for film cooling the radially inner surface of the air seal.

Turbine outer air seal

A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.

Multiple cooling schemes for turbine blade outer air seal

An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

Turbine airfoil platform cooling circuit

A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Growing community of inventors

Wethersfield, CT, United States of America

Christopher R Joe