Blade outer seal with micro axial flow cooling system
First Claim
1. A blade outer air seal assembly for a turbine engine comprising:
- a plurality of interfiting blade outer air seal segments each including a leading edge, a trailing edge, two axial edges, a back side and a hot side exposed to combustion gases, wherein each of said plurality of interfiting blade air seal segments includes a cavity including a top surface and a bottom surface, said top surface disposed on a side opposite said back side, and said bottom surface comprising a side opposite said hot side exposed to combustion gases;
a plurality of outlets disposed at said leading edge and said trailing edge for exhausting cooling airflow into the flow of combustion gases; and
a plurality of pedestals extending from said top surface and said bottom surface for creating turbulent cooling air flow through said cavity.
4 Assignments
0 Petitions
Accused Products
Abstract
A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.
-
Citations
22 Claims
-
1. A blade outer air seal assembly for a turbine engine comprising:
-
a plurality of interfiting blade outer air seal segments each including a leading edge, a trailing edge, two axial edges, a back side and a hot side exposed to combustion gases, wherein each of said plurality of interfiting blade air seal segments includes a cavity including a top surface and a bottom surface, said top surface disposed on a side opposite said back side, and said bottom surface comprising a side opposite said hot side exposed to combustion gases; a plurality of outlets disposed at said leading edge and said trailing edge for exhausting cooling airflow into the flow of combustion gases; and a plurality of pedestals extending from said top surface and said bottom surface for creating turbulent cooling air flow through said cavity. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
-
-
14. A turbine blade shroud assembly for a turbine engine comprising:
a plurality of interfitting blade outer air seal segments, each of said plurality of interfitting blade outer air seal assemblies a leading edge, a trailing edge, axial edges, and a cavity including a top surface and a bottom surface, said top surface comprising a side opposite a back side, and said bottom surface comprising a side opposite a hot side exposed to combustion gases, said cavity includes a plurality of inlet openings disposed along said back side between said leading and trailing edges;
wherein said cavity comprises a leading edge cavity and a trailing edge cavity separated by a divider and a plurality of pedestals extending between said top surface and said bottom surface for creating turbulent cooling air flow through said cavity.- View Dependent Claims (15, 16, 17)
-
18. A blade outer air seal segment comprising:
-
a leading edge; a trailing edge; a cool side exposed to a source of cooling air; a hot side exposed to hot fluid flow; and a main cavity including a top surface and a bottom surface, said top surface comprising a side opposite said cool side, and said bottom surface comprising a side opposite said hot side, wherein said main cavity is divided into a trailing edge cavity and a leading edge cavity by a divider that divides cooling air flow between said leading edge cavity and said trailing edge cavity. - View Dependent Claims (19, 20, 21, 22)
-
Specification