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US 7,824,152 B2Granted
Multivane segment mounting arrangement for a gas turbine
AssigneeSiemens Energy, Inc.
InventorJay A. Morrison
Life of this patent
Estimating the term…
Abstract
A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround internal struts (24) joining the outer and inner rings. Spring members (26, 28) accommodate differential thermal growth between the multivane segment and the outer and inner rings, and a compliant material (30) seals against gas leakage around the segments.
Claims20
A vane mounting arrangement for a gas turbine engine comprising:
- a plurality of multivane segments collectively defining a vane stage, each segment comprising a plurality of vanes extending between an inner shroud and an outer shroud, each segment comprising a ceramic matrix composite material;
- an inner ring comprising a metallic material;
- an outer ring comprising a metallic material;
- a plurality of struts connected between the inner ring and the outer ring and extending through respective selected ones of the vanes;
- and
- a plurality of biasing members disposed between the segments and the respective inner ring and outer ring for preloading the segments into position between the rings and for accommodating differential thermal expansion there between.
3 more elements
A vane mounting arrangement for a gas turbine engine comprising:
- a ceramic matrix composite vane stage comprising a plurality of multivane segments positioned in an abutting end-to-end arrangement;
- a metallic support structure for supporting the plurality of multivane segments in the abutting end-to-end arrangement within a gas turbine engine, the metallic support structure further comprising:
- a radially outer support for resisting movement of the vane stage in a radially outward direction;
- a radially inner support for resisting movement of the vane stage in a radially inward direction;
- a plurality of radially extending members arranged between the radially outer support and the radially inner support, each radially extending member disposed within a respective selected vane of the vane stage for relative radial movement there between, wherein fewer vanes are selected than are present;
- and
- a first spring biasing member disposed between the vane stage and the radially outer support and a second spring biasing member disposed between the vane stage and the radially inner support;
- the first and second spring biasing members cooperating to position the vane stage at a radial position between the radially outer support and the radially inner support responsive to a differential thermal growth condition existing between the ceramic matrix composite vane stage and the metallic support structure.
5 more elements
A mounting arrangement comprising:
- a ceramic nozzle structure comprising a plurality of arcuate-shaped vane segments;
- a plurality of radially oriented struts connecting between an inner metallic support structure and an outer metallic support structure, wherein the struts support the plurality of vane segments in an abutting end-to-end arrangement within a gas turbine engine, each of the struts passing through a portion of a respective vane segment for resisting rotation of the ceramic nozzle structure while allowing radial movement of the vane segments relative to the inner and outer metallic support structures;
- and
- biasing members for positioning the ceramic structure at a relative position between the inner and outer metallic support structures responsive to a temperature condition causing differential thermal growth between the ceramic structure and the inner and outer metallic support structures.
1 more element
Dependencies are inferred from the claim text.