Ventilated thermal barrier coating
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Robert Edward Schafrik, Ramgopal Darolia
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends which are covered by the thermal barrier coating, and the pores are ventilated from an opposite second surface of the wall for cooling the thermal barrier coating.
Claims21
A gas turbine engine component comprising a perforate metal wall having pores covered at first ends thereof by a thermal barrier coating disposed over a first surface of said wall.
A gas turbine engine combustor liner comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
A turbine nozzle vane comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
A turbine nozzle band comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
A turbine blade comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
A turbine shroud comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
A gas turbine engine exhaust liner comprising:
- a metal wall having opposite first and second surfaces and a multitude of pores extending through said wall between opposite first and second ends of said pores;
- a bond coating covering said first surface and lining said pores;
- and
- a thermal barrier coating covering said bond coating along said first surface and covering said pore first ends, with said pore second ends remaining open.
Dependencies are inferred from the claim text.