Patent ID: 11952900
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 11:
12. A gas turbine engine comprising:
a compressor section;
a combustion section; and
a turbine section,
the compressor section, the combustion section, and the turbine section in serial flow order and defining at least in part a core air flowpath, the turbine section comprising a variable guide vane assembly comprising:
an airfoil band defining a surface exposed to the core air flowpath and a cavity, the airfoil band including an airfoil band flange defining a first side facing the core air flowpath and an opposing second side facing the cavity;
an airfoil comprising a first end and an opposite second end and an airfoil flange disposed in the cavity of the airfoil band radially outward of the airfoil band flange, the airfoil extending along an axis between the first end and the second end and being moveable about the axis relative to the airfoil band; and
a sealing element positioned at the first end to contact and to form a seal between the airfoil flange at the first end of the airfoil and the second side of the airfoil band flange.