Turbomachine

Patent metadata

Field	Value
Publication number	US-9739176-B2
Application number	US-201414520992-A
Country	US
Kind code	B2
Filing date	Oct 22, 2014
Priority date	Oct 24, 2013
Publication date	Aug 22, 2017
Grant date	Aug 22, 2017

Abstract

A turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing.

First claim

What is claimed is:

1. A turbomachine ( 1 ) comprising:
a stator-side housing ( 2 ), having:
a flange ( 22 ),
first and second stator-side guide vane supports ( 21 , 18 ) each being fastened to the stator-side housing ( 2 ), the first and second stator-side guide vane supports ( 21 , 18 ) having respective first and second guide vane support flanges ( 9 , 23 ),
first and second stator-side guide vanes ( 5 , 19 ) fastened to the first and second stator-side guide vane supports ( 21 , 18 ), respectively, and
first and second axially spaced guide vane rings ( 35 , 36 ) associated with the first and second stator-side guide vanes ( 5 , 19 ), respectively; and

a rotor having a plurality of rotor-side moving blades,
wherein at least two of the first and second stator-side guide vane supports ( 21 , 18 ) are jointly fastened to and centered on the flange ( 22 ) of the stator-side housing ( 2 ), and
wherein a centering of a first stator-side guide vane support ( 21 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the radial direction ( 15 ) and the circumferential direction ( 12 ) of the turbomachine occurs as a result of a plurality of first centering elements ( 24 ) extending through the first guide vane support flange ( 9 ) into the flange ( 22 ) of the stator-side housing ( 2 ), and a centering of a second stator-side guide vane support ( 18 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the radial direction ( 15 ) and the circumferential direction ( 12 ) of the turbomachine occurs as a result of a plurality of second centering elements ( 33 ) extending through the second guide vane support flange ( 23 ) and the first guide vane support flange ( 9 ) into the flange ( 22 ) of the stator-side housing ( 2 ).

2. The turbomachine according to claim 1 , wherein the turbomachine is a gas turbine.

3. The turbomachine according to claim 1 , wherein the plurality of first centering elements ( 24 ) is at least three first centering elements ( 24 ) and the plurality of second centering elements ( 33 ) is at least three second centering elements ( 33 ).

4. A turbomachine ( 1 ) comprising:
a stator-side housing ( 2 ), having:
a flange ( 22 ),
first and second stator-side guide vane supports ( 21 , 18 ) each being fastened to the stator-side housing ( 2 ), the first and second stator-side guide vane supports ( 21 , 18 ) having respective first and second guide vane support flanges ( 9 , 23 ),
first and second stator-side guide vanes ( 5 , 19 ) fastened to the first and second stator-side guide vane supports ( 21 , 18 ), respectively, and
first and second axially spaced guide vane rings ( 35 , 36 ) associated with the first and second stator-side guide vanes ( 5 , 19 ), respectively;

connecting elements ( 17 ); and
a rotor having a plurality of rotor-side moving blades,
wherein at least two of the first and second stator-side guide vane supports ( 21 , 18 ) are jointly fastened to and centered on the flange ( 22 ) of the stator-side housing ( 2 ),
wherein the first and second stator-side guide vane supports ( 21 , 18 ) are fastened to the flange ( 22 ) of the stator-side housing ( 2 ) by the connecting elements ( 17 ) extending through the respective first and second guide vane support flanges ( 9 , 23 ), which are jointly fastened to and centered on the flange ( 22 ) of the stator-side housing ( 2 ), and into the flange ( 22 ) of the stator-side housing ( 2 ),
wherein a centering of the first stator-side guide vane support ( 21 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the axial direction ( 16 ) of the turbomachine occurs as a result of a first surface ( 4 ) of the first guide vane support flange ( 9 ) coming to bear against a surface ( 3 ) of the flange ( 22 ) of the stator-side housing ( 2 ), and a centering of the second stator-side guide vane support ( 18 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the axial direction ( 16 ) of the turbomachine occurs as a result of a flange surface ( 28 ) of the second guide vane support flange ( 23 ) coming to bear against a second flange surface ( 20 ) of the first guide vane support flange ( 9 ), and
wherein a centering of a first stator-side guide vane support ( 21 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the radial direction ( 15 ) and the circumferential direction ( 12 ) of the turbomachine occurs as a result of at least three first centering elements ( 24 ) extending through the first guide vane support flange ( 9 ) into the flange ( 22 ) of the stator-side housing ( 2 ), and a centering of a second stator-side guide vane support ( 18 ) on the flange ( 22 ) of the stator-side housing ( 2 ) in the radial direction ( 15 ) and the circumferential direction ( 12 ) of the turbomachine occurs as a result of at least three second centering elements ( 33 ) extending through the second guide vane support flange ( 23 ) and the first guide vane support flange ( 9 ) into the flange ( 22 ) of the stator-side housing ( 2 ).

5. The turbomachine according to claim 4 , wherein each first centering element ( 24 ) projects, via a first cylindrical section ( 6 ), into a bore-like cutout ( 8 ) in the flange ( 22 ) of the stator-side housing ( 2 ), and each first centering element ( 24 ) projects with a second section ( 37 ) into a slot-like cutout ( 10 ) in the first guide vane support flange ( 9 ), the second section ( 37 ) of each first centering element ( 24 ) having a cylindrical basic contour with opposite flats ( 7 ) which run parallel to corresponding surfaces ( 11 ) of the slot-like cutout ( 10 ) such that a distance therebetween allows a defined relative movement between the first stator-side guide vane support ( 21 ) and the stator-side housing in the circumferential direction ( 12 ) of the turbomachine, and the second section ( 37 ) of each first centering element ( 24 ) having further surfaces ( 14 ) which extend between the flats ( 7 ) and run relative to corresponding surfaces ( 13 ) of the respective cutout ( 10 ) such that a spacing therebetween the allows a defined relative movement between the first stator-side guide vane support ( 21 ) and the stator-side housing ( 2 ) in the radial direction of the turbomachine.

6. The turbomachine according to claim 5 , wherein each second centering element ( 33 ) projects, via a first cylindrical section ( 6 ), into the bore-like cutout ( 8 ) in the flange ( 22 ) of the stator-side housing ( 2 ) and a bore-like cutout ( 32 ) in the first guide vane support flange ( 9 ), and each second centering element ( 33 ) projects with the second section ( 37 ) into a slot-like cutout ( 10 ) in the flange ( 23 ) of the second stator-side guide vane support ( 18 ), the second section ( 37 ) of each second centering element ( 33 ) having a cylindrical basic contour with opposite flats ( 7 ) which run parallel to corresponding surfaces ( 11 ) of the slot-like cutout ( 10 ) such that a spacing therebetween allows a defined relative movement between the second stator-side guide vane support ( 18 ) and the stator-side housing ( 2 ) in the circumferential direction ( 12 ) of the turbomachine, and the second section ( 37 ) of each second centering element ( 33 ) having further surfaces ( 14 ) which extend between the flats ( 7 ) and run relative to corresponding surfaces ( 13 ) of the respective slot-like cutout ( 10 ) such that a spacing therebetween allows a defined relative movement between the second stator-side guide vane support ( 18 ) and the stator-side housing ( 2 ) in the radial direction ( 15 ) of the turbomachine.

7. The turbomachine according to claim 6 , wherein, in each first centering element ( 24 ) and in each second centering element ( 33 ), bore-like cutouts ( 26 , 34 ) are provided, through which the connecting elements

Assignees

• Aschenbruck Emil
• El Masalme Jaman
• Blaswich Michael
• Man Diesel & Turbo Se

Inventors

• Aschenbruck Emil
• El Masalme Jaman
• Blaswich Michael

Classifications

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2240/91

  on a stationary structure · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title