Turbine blade track assembly
AssigneeROLLS-ROYCE plc
InventorsDavid J. Thomas, Richard C. Uskert
Life of this patent
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Abstract
A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.
Claims20
An apparatus comprising:
- a blade track including a segment portion having a first surface and a second surface opposite the first surface, wherein the first surface is arcuate;
- and
- an attachment portion extending from the second surface, wherein a coupling region of the attachment portion has a dovetail shaped cross section.
The apparatus of claim wherein a plurality of blade track segments are arranged circumferentially about a common axis to define an exhaust gas flow path for a turbine.
A turbine blade track assembly comprising:
- a blade track segment portion having a first surface, a second surface opposite the first surface, and a pair of spaced apart third surfaces extending from the first surface to the second surface, wherein the first surface is an arcuate surface adapted to form a portion of an outer wall of an exhaust gas flow path;
- a blade track attachment portion extending from the second surface, wherein a coupling region of the attachment has a dovetail shaped cross section;
- and
- a blade track hanger configured to connect to a fixed structure positioned in a gas turbine engine, the hanger having a coupling portion structured to receive the dovetail shaped coupling region of the blade track attachment portion.
A gas turbine engine comprising:
- a turbine section having at least one turbine rotor with a plurality of turbine blades;
- a plurality of blade tracks positioned circumferentially around the turbine blades;
- at least one dovetail shaped connecting member extending radially outward from each blade track;
- and
- a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.
Dependencies are inferred from the claim text.