Attachment for blade outer air seal
A turbine section for a gas turbine engine includes a turbine having at least one blade rotatable around an axis. The at least one blade has a tip. The turbine section for a gas turbine engine also includes at least one blade outer air seal arranged radially outward from the tip. The blade outer air seal has a center web and first and second mounting arms extending from the center web. Each of the first and second mounting arms include at least one aperture configured to receive a pin to attach the blade outer air seal to an engine static structure. A gas turbine engine and a method of attaching a blade outer air seal to a static structure of a gas turbine engine are also disclosed.
1. A gas turbine engine, comprising:
a turbine section arranged along a central engine axis, the turbine section having a turbine with at least one blade rotatable around the central engine axis, the at least one blade having a tip;
at least one blade outer air seal arranged radially outward from the tip, the blade outer air seal having a center web and first and second mounting arms extending from the center web, wherein each of the first and second mounting arms include at least one aperture configured to receive a pin;
a static structure, the static structure including first and second flanges, each of the first and second flanges including at least one aperture configured to receive the pin to attach the blade outer air seal to the static structure;
a seal plate that extends for an entire circumference of the blade outer air seal, with the at least one blade outer air seal including a plurality of blade outer air seal segments, the seal plate abutting the first flange at an upstream location;
wherein the aperture in the second flange is a pocket;
wherein the second flange is aft of the first flange along the central engine axis;
wherein the pin extends between a first end and a second end, wherein the second end is tapered, and wherein the second end is received in the pocket;
wherein a length of a taper of the second end is smaller than a length of the pocket;
the pin comprising a high-temperature material selected from cobalt, nickel, an alloy of cobalt or nickel, or a combination thereof; and
wherein the seal plate has a radially extending portion abutting the first flange, and an axially extending portion extending in both a forward direction and a rear direction from the radial portion, with the axial portion extending in the rear direction extending radially inward of the first flange.
2. The gas turbine engine of claim 1 , wherein the second end has a flat face that is configured to abut an aft face of the pocket.
3. The gas turbine engine of claim 1 , wherein the blade outer air seal comprises a ceramic matrix composite or a monolithic ceramic material.
4. The gas turbine engine of claim 1 , wherein the pin includes at least one of a thermal barrier coating or an environmental barrier coating.