An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

The gas turbine engine combustor can have a gas generator case having a first coefficient of thermal expansion, a liner inside the gas generator case, the liner delimiting a combustion chamber, a service tube extending inside the gas generator case, outside the liner, the service tube having a second coefficient of thermal expansion, the second coefficient of thermal expansion being higher than the first coefficient of thermal expansion.

A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.

A shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.

A cooling structure includes: a housing including an inner cylindrical portion through which a shaft is inserted; a coolant flow path formed in the housing and opened on one side of the housing in a rotational axis direction, the coolant flow path being located radially outside the inner cylindrical portion; a lid member disposed in an opening of the coolant flow path, the lid member located radially outside the inner cylindrical portion and adjacent to the coolant flow path; a first end portion on the lid member, the first end portion contacting, in the radial direction, an inner circumferential surface of the coolant flow path on one side in the radial direction; and a second end portion on the lid member, the second end portion contacting, in the rotational axis direction, an abutment surface on the housing on the other side in the radial direction.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount pin assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mount pin assembly is configured to couple the seal segment to the carrier.

A ceramic matrix composite (CMC) component includes at least one seal surface, the at least one seal surface disposed adjacent an interfacing surface for providing a seal therebetween; and a coating disposed on the seal surface. The coating includes an aluminum oxide and/or a silicon dioxide.

A rotor for a machine under this disclosure could be said to include a hub having a plurality of blades extending radially outwardly of the hub. At least one of the hub and the plurality of blades is formed of at least two metal materials. The two metal materials are selected to have different thermal expansion coefficients such that the overall rotor will be more resistant to forces it may experience as temperature or speed increases. There are layers of each of the two metal materials, with an intermediate gradient wherein the two materials are mixed. Alternatively, a shape memory alloy may be used. A method is also disclosed.

A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

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.