Turbine nozzle support
AssigneeGeneral Electric Company
InventorsSteven M. Toborg, Roger W. Schonewald
Life of this patent
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Abstract
A gas turbine nozzle includes a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments. Each inner shroud segment includes a circumferential retention slot and a radial retention slot in generally circumferential alignment and an interlocking tab and slot arrangement at the respective ends to provide engagement between adjacent flange segments. A 360 degree retention ring includes a plurality of circumferential retention tabs and radial retention tabs to engage respective ones of the plurality of flange segments to secure the nozzle segments in a circumferential ring about the outlet of a gas turbine combustor.
Claims6
A gas turbine nozzle arrangement comprising:
- a plurality of nozzle segments each comprising:
- an outer arcuate shroud segment;
- an inner arcuate shroud segment comprising:
- a generally arcuate, axially extending platform;
- a circumferential nozzle mounting flange projecting radially inward from said platform;
- and a circumferential retention slot passing through said flange and a radial retention slot in generally circumferential alignment with said circumferential retention slot and extending partially through said flange;
- and
- a plurality of vanes extending between and connected to said outer and inner shroud segments;
- annular nozzle retaining means for securing said plurality of nozzle segments in a generally annular configuration;
- a nozzle support flange attached to a gas turbine combustor around the axis of the gas turbine;
- and
- a plurality of fasteners for securing said nozzle retaining ring to said nozzle support flange.
In a gas turbine engine including in serial flow relationship:
- an annular combustor generally concentric about an engine centerline, a nozzle arrangement and a turbine rotatable about an axis of rotation generally coincident with said engine centerline;
- said nozzle arrangement comprising:
- a plurality of nozzle segments arranged in a generally annular configuration about said centerline and each comprising:
- an outer arcuate shroud segment;
- an inner arcuate shroud segment;
- a plurality of generally radially extending vanes disposed between said outer shroud segment and said inner shroud segment and each connected to said outer shroud segment and said inner shroud segment;
- said vanes having spaced leading and trailing edges and defining therebetween flow passages for hot gases from a gas turbine combustor;
- and
- each said inner shroud segment including a platform and a circumferential nozzle mounting flange projecting radially inward therefrom;
- each said flange having a circumferential retention slot and a radial retention slot disposed therein in generally circumferential alignment;
- a circumferential nozzle retainer having a plurality of circumferential retention tabs and a plurality of radial retention tabs disposed thereon in generally circumferential alignment for securing said plurality of nozzle segments in a generally annular configuration about the centerline;
- a nozzle support flange attached to a gas turbine combustor around the engine centerline;
- and
- a plurality of fasteners securing said nozzle retainer to said nozzle support flange to hold said mounting flange therebetween.
Dependencies are inferred from the claim text.