US 2010/0074731 A1Published application

Gas Turbine Sealing Apparatus

AssigneeSiemens Energy, Inc.

InventorsDavid J. Wiebe, Brian J. Wessell, Todd Ebert, Alexander Beeck, George Liang, Walter H. Marussich

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Abstract

A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

Claims20

Dependent claims

Sealing apparatus in a gas turbine comprising forward and aft rows of rotatable blades coupled to a disc/rotor assembly and a row of stationary vanes positioned between the forward and aft rows of rotatable blades, the sealing apparatus comprising:

an annular intermediate disc coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine;
seal housing apparatus coupled to said annular intermediate disc so as to be rotatable with said annular intermediate disc and the disc/rotor assembly during operation of the gas turbine, said seal housing apparatus comprising:
a leg structure extending radially outwardly from said annular intermediate disc toward the row of stationary vanes, said leg structure including a first end portion coupled to said annular intermediate disc and a second end portion spaced apart from said first end portion in a radial direction;
a base member coupled to said second end portion of said leg structure, said base member extending generally axially between the forward and aft rows of rotatable blades and positioned adjacent to the row of stationary vanes, said base member having a first end portion proximate to the forward row of rotatable blades and a second end portion proximate to the aft row of rotatable blades.

1 more element

A gas turbine comprising:

forward and aft rows of rotatable blades coupled to a disc/rotor assembly, said forward row of rotatable blades associated with a first portion of said disc/rotor assembly, and said aft row of rotatable blades associated with a second portion of said disc/rotor assembly;
a row of stationary vanes positioned between said forward and aft rows of rotatable blades;
and
an annular intermediate disc coupled to said disc/rotor assembly so as to be rotatable with said disc/rotor assembly during operation of the gas turbine, said annular intermediate disc including:
a forward side coupled to said first portion of said disc/rotor assembly;
and
an aft side coupled to said second portion of said disc/rotor assembly;
a seal housing apparatus coupled to said annular intermediate disc so as to be rotatable with said annular intermediate disc and said disc/rotor assembly during operation of the gas turbine.

5 more elements

Dependencies are inferred from the claim text.

Facts

Application: 12/611,241Filed 3 Nov 2009
Priority: 25 Sep 2008
Published: 25 Mar 2010
Term ends: Not estimatedThe source records don’t support an estimate.

Classification3 codes

F01D 11/001
Preventing or minimising internal leakage of working-fluid, e.g. between stages: for sealing space between stator blade and rotor
F01D 11/005
Preventing or minimising internal leakage of working-fluid, e.g. between stages: sealing means between non relatively rotating elements
F01D
Non-positive displacement machines or engines

Family

Application61/100,107Us provisional application · filed 25 Sep 2008
Application12/355,878Continuation in part · filed 19 Jan 2009
Application12/611,241Continuation in part
US 2010/0074730 A1Published application
US 8,162,598 B2Related patent
US 8,376,697 B2Related patent
US 2010/0074731 A1This patent

From the US filing history. Foreign family members aren’t listed.