Abstract: A method of cleaning a component includes providing the component following the operation of the component in a high temperature environment, the component including a thermal barrier coating (TBC), cleaning the TBC of the component using a sponge jet blasting process, and measuring a cleaned thickness of the TBC to verify that the cleaned thickness exceeds a predetermined minimum value that will allow the return of the component to the high temperature environment.

Abstract: A method of cleaning a component includes providing the component following the operation of the component in a high temperature environment, the component including a thermal barrier coating (TBC), cleaning the TBC of the component using a sponge jet blasting process, and measuring a cleaned thickness of the TBC to verify that the cleaned thickness exceeds a predetermined minimum value that will allow the return of the component to the high temperature environment.

Abstract: A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass cooling fluids through impingement orifices in the hollow, disc post body to impinge on inner surfaces of platforms of the turbine airfoils. The cooling fluids may then be directed to the internal cooling systems of the turbine airfoils rather than being discharged as film cooling fluids through the platforms of the turbine airfoils.

Abstract: A seal plate system (24) for a rotor in a turbine engine. The rotor includes a rotor disc (10) for supporting a plurality of blades (16), and an annular groove (32) provided in the disc (10) adjacent at least one end (30) of the disc (10). A plurality of plate structures (60) are provided supported between the annular groove (32) of the disc (10) and a groove (56) formed in a platform (26) of the blade (16) adjacent an end (30) of the disc (10). The plate structure (60) includes a plate (64) and an elongated resilient locking pointer (66) extending from the plate (64) for engaging in a lock notch (98) formed in an outer wall (38) of the annular groove (32). The locking pointer (66) forms a self-locking feature that is biased into the lock notch (98) as the plate structure (60) is moved into position on the disc (10).

Abstract: A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass cooling fluids through impingement orifices in the hollow, disc post body to impinge on inner surfaces of platforms of the turbine airfoils. The cooling fluids may then be directed to the internal cooling systems of the turbine airfoils rather than being discharged as film cooling fluids through the platforms of the turbine airfoils.

Abstract: A seal plate system (24) for a rotor in a turbine engine. The rotor includes a rotor disc (10) for supporting a plurality of blades (16), and an annular groove (32) provided in the disc (10) adjacent at least one end (30) of the disc (10). A plurality of plate structures (60) are provided supported between the annular groove (32) of the disc (10) and a groove (56) formed in a platform (26) of the blade (16) adjacent an end (30) of the disc (10). The plate structure (60) includes a plate (64) and an elongated resilient locking pointer (66) extending from the plate (64) for engaging in a lock notch (98) formed in an outer wall (38) of the annular groove (32). The locking pointer (66) forms a self-locking feature that is biased into the lock notch (98) as the plate structure (60) is moved into position on the disc (10).

Abstract: Aspects of the invention relate to a cooling system for a blade platform that can provide cooling to and reduce stress on the platform. Aspects of the invention relate to including one or more channels in the blade platform such that the channels extend from the trailing edge face of the platform toward, but terminate prior to, the leading edge face of the platform. The channels can be generally oval or oblong in conformation. Extending between the hollow shank and the channels can be a plurality of cooling holes. During engine operation, coolant is supplied to the shank of the blade assembly. Because the pressure at the shank is greater than the pressure at the trailing edge of the platform, coolant flow is induced through the cooling holes and into the channels. After flowing through the channels, the coolant can be dumped at the trailing edge.