Gas turbine high temperature turbine blade outer air seal assembly
AssigneeHoneywell International Inc.
InventorsMark C. Morris, Steve H. Halfmann, Craig A. Wilson, Shawn J. Pollock, Carl A. Larson
Life of this patent
Estimating the term…
Abstract
A turbine shroud assembly includes forward and aft hangers, an axisymmetric plenum assembly, ceramic shroud segments, ceramic spacers, and forward and aft rope seals. The plenum assembly supplies impingement cooling to the shroud and the hangers. The impingement cooling to the forward and aft hangers is controlled independently to improve blade tip clearance. The rope seals are radially inward from the hangers and reduce cooling flow leakage. The turbine shroud assembly can operate in a higher temperature environment using less cooling flow than the prior art.
Claims29
A turbine shroud assembly comprising:
- a plurality of shroud segments assembled circumferentially about a longitudinal engine centerline axis, at least one shroud segment having a forward hook and an aft hook;
- at least one spacer channel positioned on the radially outward side of said shroud segments, such that said at least one spacer channel is in contact with an interface of two said shroud segments;
- at least one ceramic spacer seal positioned in contact with said at least one spacer channel, such that said at least one ceramic spacer seal is within said at least one spacer channel;
- at least one forward hanger positioned radially outward from said shroud segments, said at least one forward hanger having a forward hanger rail capable of engaging said forward hook, said forward hanger rail having an o-ring groove positioned circumferentially on a radially inward side;
- at least one aft hanger positioned radially outward from said shroud segments, said at least one aft hanger having an aft hanger rail capable of engaging said aft hook, said aft hanger rail having an angled surface positioned on the forward edge of a radially inward side;and
- a plenum assembly positioned between and in contact with said at least one forward hanger and said at least one aft hanger.
A turbine shroud assembly comprising:
- a plurality of ceramic shroud segments assembled circumferentially about a longitudinal engine centerline axis, each said ceramic shroud segment having a forward hook and an aft hook;and
- a plurality of ceramic spacer seals positioned in contact with said ceramic shroud segments, such that each one said ceramic spacer seal is in contact with the radially outward side of two said ceramic shroud segments.
An apparatus for cooling turbine engine shroud segments and hanger rails comprising:
- a plenum comprised of enclosing surfaces of the segments and hanger rails;
- an axisymmetric plenum balloon positioned in the plenum and having an impingement cooling array there through;
- said impingement cooling array comprising holes with axes perpendicular to an outer surface of the axisymmetric plenum balloon;
- a plurality of flow metering openings in fluid communication with said axisymmetric plenum balloon;
- a plurality of inlet openings in flow communication with said flow metering openings;
- and
- wherein an outer surface of the axisymmetric plenum balloon follows a contour of an internal surface of the plenum so that each of the holes of the impingement array are oriented to provide flow in a direction that is perpendicular to a corresponding underlying portion of the internal surface of the plenum.
A rope seal apparatus for use between a turbine shroud and hangers comprising:
- first and a second compressed hybrid ceramic ropes positioned between and in contact with said turbine shroud and said hangers, such that said hangers are radially outward from said compressed hybrid ceramic ropes;
- the first hybrid ceramic rope being adjacent the forward hanger;
- the second hybrid ceramic rope being adjacent the aft hanger;
- the second hybrid ceramic rope being compressed to a greater degree than the first hybrid ceramic rope.
A method of shielding a turbine engine from a hot gas flow path there through comprising the steps of:
- providing a plurality of ceramic shroud segments assembled circumferentially about a longitudinal engine centerline axis through said hot gas flow path, a forward hanger radially outward from and forward of said ceramic shroud segments, an aft hanger radially outward from and aft of said ceramic shroud segments, and a plenum assembly between and in contact with said forward hanger and said aft hanger;and
- supplying a cooling flow to said plenum assembly such that said cooling flow impinges said ceramic shroud segments, said forward hanger, and said aft hanger.
Dependencies are inferred from the claim text.