A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.

A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.

A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.

An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a hot section structure of the gas turbine engine. The hot section structure is configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure. The surfaces include a first surface and a second surface. The hot section structure includes metal and thermal barrier material. The first surface is formed by the metal. The second surface is formed by the thermal barrier material.

An austenitic stainless steel alloy and turbocharger kinematic components are provided. An austenitic stainless steel alloy includes, by weight, about 23% to about 27% chromium, about 18% to about 22% nickel, about 0.5% to about 2.0% manganese, about 1.2% to about 1.4% carbon, about 1.6% to about 1.8% silicon, about 0% to about 0.5% molybdenum, sulfur in an amount of less than about 0.01%, phosphorous in an amount of less than about 0.04%, and a balance of iron, and other inevitable/unavoidable impurities that are present in trace amounts. The turbocharger kinematic components are made at least in part using this stainless steel alloy.

An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

A seal for sealing a space defined between first and second components, the seal having: an annular member having a substantially U-shaped cross section along at least a portion thereof, the portion configured to provide a seal interface at each of the first and second components.

The present disclosure relates to a metallic shaft for connecting components of a gas turbine engine. Example embodiments include a metallic shaft (400) for connecting components of a gas turbine engine, the shaft (400) having a longitudinal axis (410) and comprising: a first section (401) extending from a first end (403) of the shaft (400) to a joint (405), the first section (401) composed of a material having a first thermal expansion coefficient along the longitudinal axis (410); a second section (402) extending from a second opposing end (404) of the shaft to the joint (405), the second section (402) composed of a material having a second thermal expansion coefficient along the longitudinal axis (410) that is different to the first thermal expansion coefficient.

A variable inlet guide vane assembly (200) and methods of operating the variable inlet guide vane assembly (200) are disclosed. The variable inlet guide vane assembly (200) includes an inlet guide vane (210) and an actuator (220). The actuator (220) is at least partially embedded in the inlet guide vane (210) and is configured to change an angle of the inlet guide vane (210) relative to a gas flow. The actuator (220) includes a shape memory alloy. The methods of operating the variable inlet guide vane assembly (200) include modulating the shape memory alloy by transferring thermal energy between the actuator (220) and a fluid, and actuating the inlet guide vane (210) to change an angle of the inlet guide vane (210) relative to gas flow.

A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.