United Technologies Corporation

Raytheon Technologies Corporation

David M Nissley

George E Foster

Daniel R Godin

Harold D Harter

Frederick M Schwarz

David P Houston

Timothy Dale

Paul J Hiester

James R Midgley

Timothy B Winfield

Marnie A Rizo

Madeline Campbell

Charles A Ellis

Kevin N McCusker

John H Hughes

Madeline N Campbell

A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Gas turbine engine with lifing calculations based upon actual usage

A segmented abradable ceramic coating system having superior abradability and erosion resistance is disclosed. The system includes a duct segment having a metallic substrate, a MCrAlY bond coat on the substrate and a segmented abradable ceramic coating on the bond coat. The segmented abradable ceramic coating includes a base coat foundation layer, a graded interlayer and an abradable top layer for an overall thickness of preferably about 50 mils (1.270 mm). The coating is characterized by a plurality of vertical microcracks. By precisely controlling the deposition parameters, composition of the layers and layer particle morphology, segmentation is achieved, as well as superior abradability and erosion resistance.

Segmented abradable ceramic coating

A gas turbine engine component coating having superior abradability and erosion resistance is disclosed. The coating includes a base coat foundation layer, a graded interlayer and an abradable top layer for an overall thickness of preferably about 50 mils. The coating is characterized by a plurality of vertical microcracks. By precisely controlling the deposition parameters, composition of the layers and layer particle morphology, segmentation is achieved, as well as superior abradability and erosion resistance.

Gas turbine engine component

A method of producing a segmented abradable ceramic coating system having superior abradability and erosion resistance is disclosed. The system includes a duct segment having a metallic substrate, a MCrAlY bond coat on the substrate and a segmented abradable ceramic coating on the bond coat. The segmented abradable ceramic coating includes a base coat foundation layer, a graded interlayer and an abradable top layer for an overall thickness of preferably about 50 mils (1.270 mm). The coating is characterized by a plurality of vertical microcracks. By precisely controlling the deposition parameters, composition of the layers and layer particle morphology, segmentation is achieved, as well as superior abradability and erosion resistance.

Method of producing a segmented abradable ceramic coating system

A turbine shroud segment includes a substrate and a coating layer having varying thickness. Various construction details are developed that provide minimal spalling of the coating layer during use of the shroud segment. In a particular embodiment, a shroud segment includes a coating layer that tapers towards the edges. The thickness tapers to a minimum thickness along the leading and trailing edges. Within the blade passing region of the shroud segment, the coating layer tapers towards the lateral edges to a thickness determined by the minimum thickness required for abrasive contact between the shroud segment and rotor blades. In another particular embodiment, the varying thickness of the coating layer is produced by forming the substrate with a concave surface, applying the coating, and subsequently machining back the coating layer to the desired dimensions.

Turbine shroud segment including a coating layer having varying thickness

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Marlborough, CT, United States of America

David M Nissley