Vincent Marion Drerup - Cincinnati OH, US Harold Ray Hansel - Mason OH, US James Anthony Ketzer - Cincinnati OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 9/04
US Classification:
415135, 415138, 415139, 298883, 298892, 2988922
Abstract:
A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one retainer tab to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through the gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.
Turbine Vane Assembly Including A Low Ductility Vane
Ramgopal Darolia - West Chester OH, US James Ketzer - Cincinnati OH, US
International Classification:
F01D009/04
US Classification:
415/137000, 415/136000, 415/200000
Abstract:
At least one airfoil shaped vane made of a low ductility material, for example a ceramic base material such as a ceramic matrix composite or an intermetallic material such as NiAl material, is releasably carried in a turbine vane assembly including inner and outer vane supports by at least one high temperature resistant compliant seal. The seal isolates the vane from at least one of the vane supports and allows independent thermal expansion and contraction of the vane in respect to the support.