United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Brian C McLaughlin

Thomas E Clark

Paul M Lutjen

Richard K Hayford

Jeremy Drake

Terence P Tyler

Michael S Stevens

Anthony B Swift

Dairus Deylan McDowell

Timothy M Davis

Brian Duguay

Daniel S Rogers

Michael J Bruskotter

Nathan K Galle

Peter J Milligan

Jaimie Schweitzer

Ryan M Kohn

A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.

Fatigue resistant blade outer air seal

A thermally responsive flow meter may comprise a coil and a plate coupled to the coil. The plate may define a first airflow aperture. The plate may translate in a circumferential direction in response to a thermal expansion of the coil. The thermally responsive flow meter may regulate the flow of air through a second airflow aperture.

Thermally responsive cooling flow meters

A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

Retention hardware

A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal. The second seal may include a seal support extending radially therefrom which mechanically supports the first seal during engine operation.

Seal support feature for brush seals

A blade outer air seal segment may comprise a radially outward surface and a radially inward surface oriented away from the radially outward surface. A cooling channel may be located between the radially outward surface and the radially inward surface. An inlet orifice may be fluidly coupled to the cooling channel. A stress-relief orifice may be between the inlet orifice and the cooling channel.

BOAS and methods of making a BOAS having fatigue resistant cooling inlets

A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.

A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

Blade outer air seal having retention snap ring

A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.

Fluid flow assembly

Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

Creep resistant axial ring seal

A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.

Multi-air stream cooling system

A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.

Growing community of inventors

Kennebunk, ME, United States of America

Brian C McLaughlin