A metal vane core or strut (64) is formed integrally with an outer backing plate (40). An inner backing plate (38) is formed separately. A spring (74) with holes (75) is installed in a peripheral spring chamber (76) on the strut. Inner and outer CMC shroud covers (46, 48) are formed, cured, then att
A metal vane core or strut (64) is formed integrally with an outer backing plate (40). An inner backing plate (38) is formed separately. A spring (74) with holes (75) is installed in a peripheral spring chamber (76) on the strut. Inner and outer CMC shroud covers (46, 48) are formed, cured, then attached to facing surfaces of the inner and outer backing plates (38, 40). A CMC vane airfoil (22) is formed, cured, and slid over the strut (64). The spring (74) urges continuous contact between the strut (64) and airfoil (66), eliminating vibrations while allowing differential expansion. The inner end (88) of the strut is fastened to the inner backing plate (38). A cooling channel (68) in the strut is connected by holes (69) along the leading edge of the strut to peripheral cooling paths (70, 71) around the strut. Coolant flows through and around the strut, including through the spring holes.
대표청구항▼
1. A vane assembly for a gas turbine, comprising: first and second metal backing plates;a metal vane strut spanning between the backing plates, a first end of the vane strut formed integrally with the first backing plate;a cooling channel extending medially through the vane strut;a ceramic matrix co
1. A vane assembly for a gas turbine, comprising: first and second metal backing plates;a metal vane strut spanning between the backing plates, a first end of the vane strut formed integrally with the first backing plate;a cooling channel extending medially through the vane strut;a ceramic matrix composite (CMC) or superalloy airfoil mounted as a sheath over the vane strut and defining a spring chamber there between extending peripherally along a length of the vane strut;a spring installed in the spring chamber, wherein the spring is compressed between an inner surface of the CMC or superalloy airfoil and an outer surface of the vane strut;the second backing plate releasably attached to a second end of the vane strut; andfirst and second CMC shroud covers that cover facing surfaces of the respective first and second backing plates to protect the backing plates from a working gas flow;wherein a first portion of a cooling gas flows through a network of outer shroud coolant passages in the first backing plate between the first backing plate and the first shroud cover, and a second portion of the cooling gas flows through a network of inner shroud coolant passages in the second backing plate between the second backing plate and the second shroud cover. 2. The vane assembly of claim 1, wherein the first backing plate is a radially outer or distal backing plate in the gas turbine relative to the second backing plate. 3. The vane assembly of claim 2 further comprising a metal airfoil trailing edge spanning between the backing plates, wherein a cooling channel passes medially through a length of the trailing edge. 4. The vane assembly of claim 3, wherein a first end of the trailing edge is formed integrally with the first backing plate. 5. A circular array of vane assemblies each according to claim 2, wherein the respective first backing plates of the vane assemblies are attached to an outer vane carrier ring, the respective second backing plates of the vane assemblies are attached to an inner U-ring, and the vane assemblies rigidly support the inner U-ring from the outer vane carrier ring in a concentric relationship within the gas turbine; wherein the outer vane carrier ring forms a cooling gas distribution plenum, the inner U-ring forms a cooling gas inner plenum, and a cooling gas flows from the distribution plenum through the cooling channels in the struts to the inner plenum. 6. The vane assembly of claim 1, wherein the spring wraps around part of a suction side of the airfoil strut, and further comprising a plurality of peripheral contact areas on the strut defining a peripheral surface geometry that matches the inner surface of the CMC or superalloy airfoil on at least a pressure side of the strut. 7. The vane assembly of claim 6, wherein the strut further comprises peripheral cooling paths defined between the strut and the inner surface of the CMC or superalloy airfoil and between the peripheral contact areas, wherein the peripheral cooling paths comprise both radial coolant paths extending along the radial length of the strut and transverse coolant paths extending around the outer surface of the strut from a leading edge to a trailing edge thereof, wherein a plurality of coolant tributary holes pass between the medial cooling channel in the strut and the peripheral cooling paths at the leading edge of the strut, and further comprising a coolant drain between the strut and the CMC or superalloy airfoil at the trailing edge of the strut, the coolant drain being in fluid communication with the peripheral cooling paths and with an inner cooling plenum. 8. The vane assembly of claim 7, wherein the spring is formed as a plate with corrugations, wherein a plurality of holes pass through the spring between peaks and valleys of the corrugations, and wherein the spring chamber and the holes in the spring provide peripheral coolant paths along the suction side of the strut. 9. The vane assembly of claim 1 wherein the second end of the vane strut is inserted into a socket with a seal apparatus in the second backing plate and is locked therein with a pin. 10. The vane assembly of claim 9, wherein the pin is locked in the second backing plate with removable ring clips. 11. A method for forming a gas turbine vane assembly, comprising forming a metal vane strut integrally with an outer metal backing plate, wherein the vane strut comprises medial and peripheral cooling paths and a peripheral spring chamber;forming a metal inner backing plate;forming and curing a ceramic matrix composite (CMC) vane airfoil comprising an inner surface that generally matches an outer geometry of the vane strut;forming and curing CMC outer and inner shroud covers;sliding the CMC outer shroud cover over the vane strut, and attaching the CMC outer shroud cover to the outer backing plate;forming a wave spring with an array of holes;mounting the wave spring in the spring chamber, wherein the wave spring extends from the outer geometry of the vane strut to interfere with the inner surface of the CMC vane airfoil;compressing the spring to fit within the inner surface of the CMC vane airfoil;sliding the CMC vane airfoil as a sheath over the vane strut;attaching the CMC inner shroud cover to the inner backing plate; andattaching a free end of the vane strut to a socket in the second backing plate. 12. The method of claim 11, further comprising forming a metal trailing edge integrally with the outer metal backing plate, wherein the metal trailing edge comprises a medial cooling channel. 13. A vane assembly for a gas turbine, comprising: first and second metal backing plates;a metal vane strut spanning between the backing plates, a first end of the vane strut formed integrally with the first backing plate;a cooling channel extending medially through the vane strut;a ceramic matrix composite (CMC) or superalloy airfoil mounted as a sheath over the vane strut and defining a spring chamber there between extending peripherally along a length of the vane strut;a spring installed in the spring chamber, wherein the spring is compressed between an inner surface of the CMC or superalloy airfoil and an outer surface of the vane strut, wherein the spring wraps around part of a suction side of the airfoil strut;the second backing plate releasably attached to a second end of the vane strut;a plurality of peripheral contact areas on the strut defining a peripheral surface geometry that matches the inner surface of the CMC or superalloy airfoil on at least a pressure side of the strut; andperipheral cooling paths defined between the strut and the inner surface of the CMC or superalloy airfoil and between the peripheral contact areas, wherein the peripheral cooling paths comprise both radial coolant paths extending along the radial length of the strut and transverse coolant paths extending around the outer surface of the strut from a leading edge to a trailing edge thereof, wherein a plurality of coolant tributary holes pass between the medial cooling channel in the strut and the peripheral cooling paths at the leading edge of the strut, and further comprising a coolant drain between the strut and the CMC or superalloy airfoil at the trailing edge of the strut, the coolant drain being in fluid communication with the peripheral cooling paths and with an inner cooling plenum;wherein the spring is formed as a plate with corrugations, wherein a plurality of holes pass through the spring between peaks and valleys of the corrugations, and wherein the spring chamber and the holes in the spring provide peripheral coolant paths along the suction side of the strut. 14. The vane assembly of claim 13, wherein the second end of the vane strut is inserted into a socket with a seal apparatus in the second backing plate and is locked therein with a pin. 15. A circular array of vane assemblies each according to claim 13, wherein the respective first backing plates of the vane assemblies are attached to an outer vane carrier ring, the respective second backing plates of the vane assemblies are attached to an inner U-ring, and the vane assemblies rigidly support the inner U-ring from the outer vane carrier ring in a concentric relationship within the gas turbine; wherein the outer vane carrier ring forms a cooling gas distribution plenum, the inner U-ring forms a cooling gas inner plenum, and a cooling gas flows from the distribution plenum through the medial cooling channels in the struts to the inner plenum.
Morrison, Jay A.; Merrill, Gary B.; Lane, Jay E.; Campbell, Christian X.; Thompson, Daniel G.; Carelli, Eric V.; Taut, Christine, Ceramic composite vane with metallic substructure.
Huizenga, Benjamin Scott; Glynn, Christopher Charles; Senile, Darrell Glenn; Frederick, Robert Alan; Radwanski, Michael Todd; Tuertscher, Michael Ray; Phelps, Greg Scott, Ceramic matrix composite nozzle mounted with a strut and concepts thereof.
Patat, Harry; Schopf, Cheryl A.; Katy, Jerome H.; Wallace, Adam; Wiebe, David J., Purge and cooling air for an exhaust section of a gas turbine assembly.
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