Segmented ceramic matrix composite turbine airfoil component
First Claim
1. A segmented component for a gas turbine engine, the component comprising:
- a gas path portion for interacting with gas flow from the gas turbine engine; and
a root portion extending radially inwardly from the gas path portion, the root portion having a geometry for providing radial retention with a rotor of the gas turbine engine;
wherein the component is divided into axially aligned segments comprising;
a forward platform segment having contours configured to flushly abut leading edge portions of adjacent airfoils;
an aft platform segment having contours configured to flushly abut trailing edge portions of adjacent airfoils; and
a plurality of middle platform segments disposed between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates having contours configured to abut a suction side and a pressure side of adjacent airfoils; and
wherein the forward and the aft platform segments are comprised of plates of ceramic matrix composite material having a bend to form a radially extending portion forming the root portion and an axially extending portion forming the gas path portion, the axially extending portion being axially forward or aft of the radially extending portion.
4 Assignments
0 Petitions
Accused Products
Abstract
A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.
80 Citations
14 Claims
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1. A segmented component for a gas turbine engine, the component comprising:
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a gas path portion for interacting with gas flow from the gas turbine engine; and a root portion extending radially inwardly from the gas path portion, the root portion having a geometry for providing radial retention with a rotor of the gas turbine engine; wherein the component is divided into axially aligned segments comprising; a forward platform segment having contours configured to flushly abut leading edge portions of adjacent airfoils; an aft platform segment having contours configured to flushly abut trailing edge portions of adjacent airfoils; and a plurality of middle platform segments disposed between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates having contours configured to abut a suction side and a pressure side of adjacent airfoils; and wherein the forward and the aft platform segments are comprised of plates of ceramic matrix composite material having a bend to form a radially extending portion forming the root portion and an axially extending portion forming the gas path portion, the axially extending portion being axially forward or aft of the radially extending portion. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A segmented component for a gas turbine engine, the component comprising:
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a gas path portion for interacting with gas flow from the gas turbine engine; and a root portion extending radially inwardly from the gas path portion, the root portion having a geometry for providing radial retention with a rotor of the gas turbine engine; wherein the component is divided into axially aligned segments comprising; a forward platform segment having contours configured to flushly abut leading edge portions of adjacent airfoils; an aft platform segment having contours configured to flushly abut trailing edge portions of adjacent airfoils; and a plurality of middle platform segments disposed between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates having contours configured to abut a suction side and a pressure side of adjacent airfoils; and wherein the forward segment or the aft segment includes a flange extending tangentially from the root portion and configured to be positioned forward or aft of a root portion of an adjacent rotor component connected to an outer periphery of the rotor to axially restrain the adjacent rotor component. - View Dependent Claims (12)
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13. A segmented component for a gas turbine engine, the component comprising:
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a gas path portion for interacting with gas flow from the gas turbine engine; and a root portion extending radially inwardly from the gas path portion, the root portion having a geometry for providing radial retention with a rotor of the gas turbine engine; wherein the component is divided into axially aligned segments comprising; a forward platform segment having contours configured to flushly abut leading edge portions of adjacent airfoils; an aft platform segment having contours configured to flushly abut trailing edge portions of adjacent airfoils; and a plurality of middle platform segments disposed between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates having contours configured to abut a suction side and a pressure side of adjacent airfoils; and wherein the forward and aft platform segments each further include an axial extending retention tab for abutting one of the plurality of middle segments. - View Dependent Claims (14)
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Specification