US 10,519,790 B2Granted

Turbine shroud assembly

AssigneeGeneral Electric Company

InventorsMatthew Troy Hafner, John McConnell Delvaux, Glenn Curtis Taxacher

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Abstract

A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.

Claims18

Dependent claims

A turbine component comprising:

an outer shroud arranged within a turbine and further comprising opposed extending portions;
an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and comprising opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud;
wherein a pair of load path forming regions at least partially extends between facing surfaces of one surface of each arcuate portion and a corresponding extending portion;
wherein during operation of the turbine, the pair of load path forming regions extend into direct contact between at least a portion of the facing surfaces of the one surface of each arcuate portion and corresponding extending portion, resulting in formation of a four-point loading arrangement between the at least a portion of the facing surfaces of the one surface of each arcuate portion and corresponding extending portion having evenly distributed radial load forces at the load path forming regions;
and
wherein during non-operation of the turbine, the load path forming regions are in non-contact.

3 more elements

A turbine shroud assembly comprising:

an outer shroud arranged within the turbine and comprising an upstream edge and an opposed downstream edge each extending along a circumferential length;
an inner shroud comprising an upstream portion and an opposed downstream portion each extending along a circumferential length and each having an arcuate shape defining an upstream slot and a downstream slot receiving and in direct contact with respectively the upstream edge and the downstream edge of the outer shroud for supporting the inner shroud from the outer shroud and for shielding the outer shroud from a gas path within the turbine;
wherein a pair of load path forming regions at least partially extends between facing surfaces of the upstream slot and the upstream edge, and the downstream slot and the downstream edge;
wherein during operation of the turbine, the pair of load path forming regions extend into direct contact between at least a portion of one surface of the facing surfaces of each of the upstream slot and the upstream edge, and the downstream slot and the downstream edge, resulting in formation of a four point loading arrangement between the at least a portion of the one surface of the facing surfaces of each of the upstream slot and the upstream edge, and the downstream slot and the downstream edge having evenly distributed radial load forces at the load path forming regions;
and
wherein during non-operation of the turbine, the load path forming regions are in non-contact.

3 more elements

Dependencies are inferred from the claim text.

Facts

Application: 15/623,696Filed 15 Jun 2017
Published: US 2018/0363483 A120 Dec 2018
Granted: 31 Dec 2019
Term ends: Not estimatedThe source records don’t support an estimate.

Classification17 codes

F01D 9/04
Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles: forming ring or sector
F01D 11/08
Preventing or minimising internal leakage of working-fluid, e.g. between stages: for sealing space between rotor blade tips and stator
F01D 25/243
Casings ; Casing parts, e.g. diaphragms, casing fastenings: flange connections; Bolting arrangements
F01D 11/005
Preventing or minimising internal leakage of working-fluid, e.g. between stages: sealing means between non relatively rotating elements