Continuous flow machine having multiple guide vane stages and method for partially disassembling a continuous flow machine of this type

Patent metadata

Field	Value
Publication number	US-10844747-B2
Application number	US-201716079620-A
Country	US
Kind code	B2
Filing date	Feb 14, 2017
Priority date	Mar 4, 2016
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

A continuous flow machine has at least one annular guide vane carrier. The guide vane carrier, formed at least by a lower part and an upper part detachably connected to same, has at least three guide vane stages retained on the inner circumference of the at least one guide vane carrier, arranged axially behind one another in the flow direction and each having a plurality of radially extending guide vanes. Each of the guide vanes also has a guide vane blade, a base plate and a top plate, wherein the guide vane blade extends between the base plate and top plate. Via the arrangement of the securing pin in an intermediate space accessible in the assembled state, a partial disassembly of the individual guide vane stages is possible, independent of the remaining guide vane stages. The guide vane stages are conventionally mounted via retaining protrusions on neighbouring guide vane stages.

First claim

The invention claimed is:

1. A turbomachine comprising:
a guide vane carrier of ring-shaped form, which is composed at least of a lower part and an upper part which is connected releasably to the latter, and
at least three guide vane stages, which are retained on an inner circumference of the guide vane carrier and are arranged axially one behind the other in a flow direction and each have a multiplicity of substantially radially extending guide vanes,
wherein each guide vane comprises a guide vane airfoil which extends between a root plate and a head plate,
wherein each root plate is retained directly on the guide vane carrier in a form-fitting manner and, in this way, secured against displacement in a radial direction and an axial direction,
wherein at least some root plates of the multiplicity of substantially radially extending guide vanes of each guide vane stage are secured against displacement in a circumferential direction by at least one additional securing element with a direction vector that comprises both a radial component and an axial component that are greater than zero,
wherein the root plates of adjacently arranged guide vanes of axially adjacent guide vane stages in each case engage directly into one another in a form-fitting manner and partially overlap one another,
wherein remaining between the root plates of each guide vane stage and the inner side of the guide vane carrier is in each case a substantially ring-shaped intermediate space which is accessible for maintenance personnel in a maintenance state in which the lower part and the upper part of the guide vane carrier are separate from one another, and
wherein at least one securing element of the at least one additional securing element is inaccessible from an outer side of the guide vane carrier and is positioned such that, in the maintenance state, it is able to be reached, mounted, and dismounted, by the maintenance personnel via the intermediate space.

2. The turbomachine as claimed in claim 1 ,
wherein a form fit between the root plates and the guide vane carrier is brought about by projections which project at least one of radially and axially from the root plates and which engage into associated circumferential grooves of the guide vane carrier.

3. The turbomachine as claimed in claim 2 ,
wherein the projections are formed in axial end regions of the root plates.

4. The turbomachine as claimed in claim 2 ,
wherein at least the root plates of guide vanes of a first or a last guide vane stage of the at least three guide vane stages each have two projections which are arranged axially spaced apart from one another and which engage into associated circumferential grooves of the guide vane carrier in the form-fitting manner and which secure the root plates against displacement in the radial direction.

5. The turbomachine as claimed in claim 1 ,
wherein the at least one securing element of the at least one additional securing element is formed by a securing pin which is received in a recess formed on the root plate and in a recess formed on the guide vane carrier.

6. The turbomachine as claimed in claim 5 ,
wherein at least one of the recess formed on the root plate and the recess formed on the guide vane carrier is formed by a cylindrical bore.

7. The turbomachine as claimed in claim 1 ,
wherein the axial component of the direction vector of a main direction of extent of each securing element, within a plane extending radially through the securing element, is greater than the radial component.

8. The turbomachine as claimed in claim 7 ,
wherein the axial component is two to four times as large as the radial component.

9. A method for partially disassembling a turbomachine, wherein the turbomachine comprises a guide vane carrier, which is composed at least of a lower part and an upper part, and comprises at least three guide vane stages of ring-shaped form, which are retained on an inner circumference of the guide vane carrier and are arranged axially one behind the other in a flow direction, the method comprising:
removing the upper part of the guide vane carrier, and
dismounting guide vanes of a single guide vane stage of the at least three guide vane stages from the guide vane carrier,
wherein the single guide vane stage whose guide vanes are dismounted is freely selectable, and
wherein, prior to the dismounting of the guide vane stage, a support device which keeps at least one adjacently arranged guide vane stage of the at least three guide vane stages in position while the method is being carried out is mounted.

10. The method as claimed in claim 9 ,
wherein the single guide vane stage whose guide vanes are dismounted is a guide vane stage which is arranged between the outermost guide vane stages of the at least three guide vane stages.

11. The method as claimed in claim 9 ,
wherein the support device is screwed or pinned to the at least one adjacently arranged guide vane stage.

12. The turbomachine as claimed in claim 5 ,
wherein all securing elements of the at least one additional securing element are formed by securing pins.

13. The method as claimed in claim 9 ,
wherein the at least three guide vane stages of the turbomachine each comprise a multiplicity of substantially radially extending guide vanes,
wherein each guide vane of the multiplicity of substantially radially extending guide vanes comprises a guide vane airfoil which extends between a root plate and a head plate,
wherein each root plate is retained directly on the guide vane carrier in a form-fitting manner and, in this way, secured against displacement in a radial direction and an axial direction,
wherein at least some root plates of guide vanes of each guide vane stage of the at least three guide vane stages are secured against displacement in a circumferential direction by at least one additional securing element,
wherein the root plates of adjacently arranged guide vanes of axially adjacent guide vane stages of the at least three guide vane stages in each case engage directly into one another in a form-fitting manner and partially overlap one another,
wherein remaining between the root plates of each guide vane stage of the at least three guide vane stages and an inner side of the guide vane carrier is in each case a substantially ring-shaped intermediate space which is accessible for maintenance personnel in a maintenance state in which the lower part and the upper part of the guide vane carrier are separate from one another, and
wherein at least one securing element of the at least one additional securing element is inaccessible from an outer side of the guide vane carrier and is positioned such that, in the maintenance state, it is able to be reached, and mounted and dismounted, by the maintenance personnel via the intermediate space.

14. The turbomachine as claimed in claim 5 , wherein the recess formed on the root plate and the recess formed on the guide vane carrier align to form a blind recess configured to receive a respective securing element, and wherein an inlet of the blind recess is disposed in a downstream-facing surface of the guide vane carrier with respect to a flow of working fluid in past the multiplicity of substantially radially extending guide vanes.

15. The turbomachine as claimed in claim 14 , wherein the recess formed on the guide vane carrier comprises a through-portion and a blind portion that is separated by a gap from the through-portion, and wherein the blind recess comprises the inlet, then the through-portion, then the recess formed on the root plate which is disposed in the gap, and then the blin

Assignees

• Siemens Ag

Inventors

• Bärow Stefan
• Dominka Oliver
• Ederer Guido
• Felsmann Christian
• Fuchs Florian
• Herfurth Robert
• Hernandez Maza Jose Angel
• Kluck Michael
• Kohlhoff Eike
• Krabiell Kay
• Maiz Khaled
• Nouri Behnam
• Willmann Andre

Classifications

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title