United Technologies Corporation

Donald A Robbins

Raymond W Vine

Donald G Nordstrom

Mark B Goodstein

William R Knotek, Deceased

An abradable coating is described for interaction with a abrasive gas turbine engine component to provide sealing. The abradable coating comprises yttria stabilized zirconia with intentional porosity which is applied by plasma spraying to a MCrAlY bond coat which in turn rest on a superalloy substrate. The coating system is applied by plasma spraying. The coating system is adapted to interact with an abrasive coated abrasive treated gas turbine engine component.

Thin abradable ceramic air seal

A first turbine rotor hub 32 and a second turbine rotor hub 42 each have respective internal splines 52, 62 which engage coaxial, non-concentric external splines 54, 64 on a shaft 20 and are in thrust bearing relationship. The assembly requires no bolts between the rotor stages 30 and 40 to hold the two stages together. In another embodiment the turbine stages 30, 40 are part of a turbine module 5 which includes a stator assembly 94.

Two stage turbine rotor assembly

A first turbine rotor hub 32 and a second turbine rotor hub 42 each have respective internal splines 52, 62 which engage coaxial, non-concentric external splines 54, 64 on a shaft 20 and are in thrust bearing relationship cooperating, circumferentially disposed, radially inwardly extending lugs 35, 45 on each hub 32, 42 define radially inwardly extending projections 80. A resilient split metal band 60, having circumferentially disposed apertures 61 overlies the projections 80 which extend through the apertures 61. The uninstalled diameter of the band is greater than the installed diameter such that the band is self-retaining. The assembly requires no bolts between the rotor stages 30 and 40 to hold the two stages together. In another embodiment the turbine stages 30, 40 are part of a turbine module 5 which includes a stator assembly 94.

Turbine module assembly device

An annular ring 22 for an axial flow gas turbine engine disposed inwardly of an array of stator vanes 14 and between an annular flow path 18 for hot working medium gases and an annular flow path 20 for cooling air is disclosed. The ring abuttingly engages the array of stator vanes in the radial direction to provide radial support and abuttingly engages the array of stator vanes and an outer air seal block the intermixing of gases from the working medium flow path and gases from the cooling air flow path. The annular ring includes a first annular section 28 and a second annular section 30. The first annular section has an axial width to radial height ratio greater than one and the second annular section has an axial width to radial height ratio less than one to adapt the ring for axial flexibility and radial stiffness and to enable the ring to accommodate growth and axial growth between the outer air seal and the array of stator vanes while remaining within the elastic limit.

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South Windsor, CT, United States of America

Donald A Robbins