Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

Abstract: A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

Abstract: A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.

Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.

Abstract: The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a first circumferential seal, a second circumferential seal and a seal support structure configured to retain at least a portion of each of the first and second seals. The seal support structure is mounted between a turbine assembly and bearing compartment, and wherein the first and second seals provide barriers to a cavity between the turbine assembly and bearing compartment.

Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.

Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. At least one spoke includes an inlet passage with at least one branch extending in an axial direction in fluid communication with the fluid passage in the inner frame case. A fitting fluidly connects the at least one branch to the fluid passage in the inner frame case. The fitting also includes a transfer tube connecting the cooling airflow passage to a cup boss. The transfer tube is fixed relative to the cylindrical portion and moveable relative to the cup boss. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction.

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes a cooling airflow passage that extends in a radial direction and an axial direction, an elongated cylindrical portion, and a flange.

Abstract: A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion. At least one gusset extends between the cylindrical portion and the flange. At least one gusset extends to a perimeter of the flange.

Abstract: A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. At least one spoke includes a cooling airflow passage that extends through the inner frame case and the bearing support member.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.