Abstract: A transfer tube includes a conduit with an inlet and an opposed outlet. The transfer tube also includes a retention tab extending from the inlet and a locking spring tab extending from the outlet. The locking spring tab includes a claw portion extending radially from the locking spring tab of the transfer tube.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a substantially radially extending rail and a substantially axially extending leg, such that the seal has a substantially J-shaped cross-section.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: A transfer tube includes a conduit with an inlet and an opposed outlet. The transfer tube also includes a retention tab extending from the inlet and a locking spring tab extending from the outlet. The locking spring tab includes a claw portion extending radially from the locking spring tab of the transfer tube.

Abstract: A method of assembling a gas turbine engine includes locating a consumable assembly tool within the engine

Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

Abstract: A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

Abstract: A multi-component kit and method is provided to restore a plastic material, and in particular, the plastic lens covers over the headlights and taillights of an automobile. The multi-component kit includes a pretreatment formulation, a resurfacing formulation, and a restoration formulation. Each formulation is structured for application to the plastic lens covers by hand, thereby eliminating the need for specialized equipment or training. The method includes application of each formulation to the plastic lens covers using clean, lint free applicators. The pretreatment formulation is applied to clean the plastic lens covers and to prepare them for application of the resurfacing formulation, which repairs scratches and removes discoloration. The restoration formulation is applied to restore a high gloss shine to the plastic lens covers as well as to protect the plastic lens covers from the elements such as dust, dirt, and/or ultra-violet radiation.

Abstract: A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

Abstract: A multi-component kit and method is provided to pretreat, resurface, and restore a plastic material, and in particular, the plastic lens covers over the headlights and taillights of an automobile. The multi-component kit includes a pretreatment formulation, a resurfacing formulation, and a restoration formulation. Each formulation is structured for application to the plastic lens covers by hand, thereby eliminating the need for specialized equipment or training. The method includes application of each formulation to the plastic lens covers using clean, lint free applicators. The pretreatment formulation is applied to clean the plastic lens covers and to prepare them for application of the resurfacing formulation, which repairs scratches and removes discoloration. The restoration formulation is applied to restore a high gloss shine to the plastic lens covers as well as to protect the plastic lens covers from the elements such as dust, dirt, and/or ultra-violet radiation.