Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.

Abstract: A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure. A honeycomb seal is mounted to the radially inward face of the carrier. The honeycomb seal is configured for sealing engagement with a knife-edge seal rotating relative to the honeycomb seal. The seal assembly has a relatively low coefficient of thermal expansion in comparison to the static component or the knife-edge seal. For example, a gas turbine engine can include a seal assembly as described above, wherein the carrier is mounted to a static component and a rotor mounted for rotation relative to the carrier, and wherein the rotor includes the knife edge seal component sealingly engaged to the honeycomb seal.

Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.

Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

Abstract: A gimbal tube system for an onboard injector (OBI) includes a transfer tube having a first transfer tube end that can be mounted to an inner diameter of a stator platform and a second transfer tube end defining a transfer tube pivot connector. The system also includes a gimbal tube including a first gimbal tube end that defines a gimbal tube pivot connector that can movably mount to the transfer tube pivot connector such that the gimbal tube and the transfer tube can move relative to each other at a pivot joint defined between the transfer tube and the gimbal tube. The gimbal tube further includes a second gimbal tube end defining a nozzle that can be inserted into the OBI.

Abstract: A TOBI for a gas turbine engine having a TOBI body, a first TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge, and a second TOBI airfoil circumferentially adjacent to the first TOBI airfoil, the second TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge. An entrance is defined between the leading edges of the adjacent TOBI airfoils and an exit is defined between the trailing edges of the TOBI airfoils, wherein airflow entering the entrance enters in a radial direction relative to the TOBI body and airflow exiting the exit exits in a circumferential direction relative to the TOBI body.

Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.

Abstract: A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure. A honeycomb seal is mounted to the radially inward face of the carrier. The honeycomb seal is configured for sealing engagement with a knife-edge seal rotating relative to the honeycomb seal. The seal assembly has a relatively low coefficient of thermal expansion in comparison to the static component or the knife-edge seal. For example, a gas turbine engine can include a seal assembly as described above, wherein the carrier is mounted to a static component and a rotor mounted for rotation relative to the carrier, and wherein the rotor includes the knife edge seal component sealingly engaged to the honeycomb seal.

Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

Abstract: An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member.

Abstract: An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member. An example blade outer air seal assembly includes a blade outer air seal assembly having an inwardly facing surface. A blade path portion of the inwardly facing surface is axially aligned with a tip of a rotating blade.

Abstract: A mass flow measurement apparatus including a flow path defined by a tubular side wall, a probe extending through the side wall into the flow path so that a first portion of the probe is located in the flow path and a second portion of the probe, extends out of the side wall, a heater element secured to the probe, and a seal preventing fluid flowing through the flow path from contacting the heater element.

Abstract: A mass flow measurement apparatus including a flow path defined by a tubular side wall, a probe extending through the side wall into the flow path so that a first portion of the probe is located in the flow path and a second portion of the probe, extends out of the side wall, a heater element secured to the probe, and a seal preventing fluid flowing through the flow path from contacting the heater element.