Patent ID: 11879340
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine comprising:
a compressor section for receiving air and delivering it to a combustor;
a turbine section downstream of said combustor, an upstream location leading from the compressor section in a downstream direction toward the turbine section rotational axis;
the turbine section including at least one rotating blade row for rotation about a rotational axis, and there being a blade outer air seal positioned to be radially outward of blades in the rotating blade row relative to the rotational axis, the blade outer air seal having a radially inward facing web spaced from a radially outer tip of the turbine blades, and a radially outer face of said blade outer air seal relative to said radially inward facing web, wherein said blade outer air seal having a leading edge attachment feature adjacent an upstream leading edge of the blade outer air seal and a trailing edge attachment feature adjacent a downstream trailing edge of the blade outer air seal;
there being at least one brush seal having bristles extending from a mount location radially inward to contact a sealing surface on the radially outer face, there being a chamber defined between said leading edge attachment feature and said trailing edge attachment feature, and adapted to be connected to a source of pressurized cooling air, with an angle defined between said bristles and relative to said sealing surface having a radially inward extending component, and with an axial component in a direction toward said leading edge attachment feature and said trailing edge attachment feature, and the angle is less than 90° on a side of the brush seal opposite the leading edge and trailing edge attachment features; and
the bristles having a first end in contact with said sealing surface and a second end mounted in a housing to define the mount location.