EP2474744A1 - Ringförmiger Strömungskanal für einen Axialverdichter - Google Patents

Ringförmiger Strömungskanal für einen Axialverdichter Download PDF

Info

Publication number
EP2474744A1
EP2474744A1 EP11150590A EP11150590A EP2474744A1 EP 2474744 A1 EP2474744 A1 EP 2474744A1 EP 11150590 A EP11150590 A EP 11150590A EP 11150590 A EP11150590 A EP 11150590A EP 2474744 A1 EP2474744 A1 EP 2474744A1
Authority
EP
European Patent Office
Prior art keywords
flow channel
blades
ring
compressor
inner ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11150590A
Other languages
German (de)
English (en)
French (fr)
Inventor
Markus Paus
Marion Morthorst
Achim Schirrmacher
Thomas Röcken
Ulrich Waltke
Bernd Van Den Toorn
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP11150590A priority Critical patent/EP2474744A1/de
Priority to PCT/EP2011/071834 priority patent/WO2012095220A1/de
Publication of EP2474744A1 publication Critical patent/EP2474744A1/de
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity

Definitions

  • the invention relates to an annular flow channel for an axial compressor, in which attached to an outer boundary wall of the flow channel airfoils are arranged in a radiating manner in at least two immediately consecutive wreaths.
  • Axial compressors and gas turbines with axial compressors are known from the extensive state of the art in a variety of ways.
  • the last stage of the compressor viewed in the direction of flow of the compressed air, includes a ring of blades followed by a ring of vanes downstream.
  • the EP 2 194 234 A1 Following the vane ring of the last compressor stage another ring of blades, which are attached as well as the vanes to the radially outer boundary wall of the flow channel.
  • the other wreath of blades is called Nachleitrad.
  • the Nachleitschaufeln the stationary Nachleitrads have the task of exempting the air flow leaving the compressor as far as possible from swirl. Through the Entdrallung the air flow, this can build up the static pressure comparatively low loss in the compressor outlet diffuser. Although the Nachleitrad contributes no contribution to the compression of the air sucked by the axial compressor, this structurally belongs to the axial compressor.
  • the heat insulation ring is part of a rotationally fixed shaft cover of the compressor rotor, which also forms the inner boundary of the compressor outlet diffuser at the same time.
  • the concentric to the central axis shaft cover is formed thin-walled because of the rather minor mechanical stress and connected to the diffuser exit side via struts not shown with the housing of the gas turbine.
  • the housing of the axial compressor is relatively solid designed to withstand the pressure and temperature stresses during operation can. Furthermore, the housing is made relatively stiff. Thus, the load application to the housing during operation of the gas turbine leads only to small deformations. Characterized in that the shaft cover is formed with smaller wall thicknesses compared to the housing and typically has different material properties than the housing, the shaft cover heats up faster than the housing with the guide blade rows and Nachleitschn attached thereto. This has the consequence that when starting and when the gas turbine shaft cover and the housing have a different thermal expansion rate, so that when starting and stopping the gas turbine, the size of the radial column changes, the radial gap when starting temporarily smaller and temporarily larger when starting be or are.
  • the radial gap is provided with such a dimensioned minimum height that in each operating state of the gas turbine, the blade tips touch the shaft cover almost never.
  • the heat input from the compressed warm air is delayed in the shaft cover itself, which is equivalent to an adjustment of the temperature-induced thermal expansion rate of the shaft cover to the outer housing.
  • the object of the invention is therefore to provide an annular flow channel for an axial compressor, which on the one hand bring about a particularly efficient and low-loss Entdrallung the last compressor stage leaving air flow and on the other hand has a comparatively simple construction in which the different rapidly expanding components in operation neither wear to be damaged.
  • the annular flow channel is surrounded by an outer boundary wall on which in at least two successive wreaths blades are arranged radiating, wherein the blades of one of the two rings are connected with its radially inner end with a radially inner end bounding the flow channel inner ring , Wherein this has a radial extent such that the blades of the other of the two rings each with radial gap formation opposite this.
  • the invention has recognized that the radially inner boundary wall of the flow channel in the axial section of the last compressor stage and the Nachleit marina should not be part of the shaft cover if possible, since the thermal coordination of the components is very difficult. Consequently, it is proposed to shorten the shaft cover, so that these only the inner boundary wall of the to the axial compressor then connecting the compressor outlet diffuser. For this reason, the inner boundary wall of the axial compressor in the region of the vane ring of the last compressor stage and the Nachleitrades must be supported by a different structure. For this purpose, it is provided that in this axial portion of the flow channel inside limiting flow wall is formed by an inner ring which is supported or supported by the housing via the blades.
  • this concept of the inner ring supported by blades is only intended for a row of blades and not for both rings.
  • the airfoils of the other wreath may remain free-standing when the inner ring comprises an extension which extends into the axial portion of the other wreath.
  • one of the two rings - preferably the vane ring of the last compressor stage - includes blades which are coupled on the head side via the inner ring and carry this and the other of the two wreaths - preferably the Nachleitschaufelkranz - is provided with freestanding blades.
  • the inner ring must have such an axial extent that this is also located in the axial portion of the free-ending blades.
  • This design has several advantages: on the one hand, it can also be used for existing axial compressors, without the housing of the axial compressor, in which the vanes of the last compressor stage and the guide vanes are fixed radially outward - foot side - must be changed. It is then only a modification of the previously used shaft cover required. Consequently, the design of the vanes of the last compressor stage alone has to be changed in order to retrofit existing machines to such constructions. Compared to a design where both the vanes and the guide vanes Head side are coupled together via a common inner ring, the invention has the advantage that it is relatively easy to manufacture.
  • the ring of blade blades connected to the inner ring is arranged upstream of the other ring, relative to the flow direction of the flow channel.
  • the inside of the flow channel limiting inner ring may also be attached to the guide vanes.
  • the guide vanes of the last compressor stage as freestanding blades can face this radial gap forming.
  • the vanes of the last compressor stage contribute to increasing the compressor pressure ratio, it is desirable to use them rather than bonded vanes equipped with an inner shroud - the inner ring - to avoid gap losses.
  • the outer boundary wall of the flow channel, an inner boundary wall of the flow channel and the inner ring each comprise at least two ring segments.
  • the axial compressor is in total in a so-called. Dividing plane in which the machine axis is divided in half. Accordingly, both the inner ring and the outer boundary wall of the axial compressor need not be formed from one element. On the one hand, this simplifies the manufacture of the components and, on the other hand, the assembly of the axial compressor.
  • FIG. 1 shows in a longitudinal section the outlet region 10 of an axial compressor 12 of a gas turbine 14.
  • the axial compressor 12 comprises an annular flow channel 16, which in the illustrated embodiment, from left to right can be flowed through.
  • the flow channel 16 is on the output side in a diffuser 18 via.
  • the axial compressor 12 comprises a housing 20, which simultaneously represents the outer boundary wall 22 for the flow channel 16 and for the diffuser 18. Both the flow channel 16 and the diffuser 18 are formed as annular channels, which extend concentrically around the machine axis 19.
  • the axial compressor 12 further comprises a rotor 24, which may be designed, for example, in disc design. Part of a rotor disk is in FIG. 1 provided with the reference numeral 26. At the outer surface of blades 28 are hooked in a known manner with the aid of hammer-shaped feet 30.
  • a rim 32 Downstream of the blades 28, there is provided a rim 32 which includes a plurality of vanes 34 radiantly attached to the boundary wall 22.
  • Each of these guide vanes 34 has an airfoil 36, which is located in the flow channel 16.
  • an inner ring 40 is arranged, which is supported by the vanes 34 and supported.
  • a further ring 42 is provided with a plurality of airfoils 44.
  • the blades 44 of the ring 42 are not assigned to a compressor stage of the axial compressor 12. They are located in the flow channel 16 immediately downstream of the blades 36 of the vanes 34 and serve to Entdrallung the air flow, so that it can flow into the ring diffuser 18 largely swirl-free.
  • the inner ring 40 comprises an axial extension 41 in a cylindrical shape, which faces the radially inner tips 48 of the airfoils 44 radial gap forming.
  • a rotatably arranged shaft cover 50 is located as an inner boundary of the ring diffuser 18.
  • the shaft cover has a projection 54 on its front side surface 52. This overlaps axially, but radially further inside the inner ring 40 partially. This makes it possible to arrange the annular sealing plate 56 in two opposing grooves 58 and seal the gap between the shaft cover 50 and inner ring 40.
  • FIG. 2 shows in a perspective partial sectional view of the vane ring 32 with a plurality of circumferentially successive vanes 34, whose head-side end are hooked to the inner ring 40.
  • FIG. 1 known features in FIG. 2 provided with identical reference numerals.
  • Each vane 34 has at its radially outer end a dovetail-shaped blade root 37 which is inserted in a groove 39 arranged in a retaining ring.
  • a hammer-shaped blade head 49 is provided, which is hooked in a correspondingly shaped groove 43 of the inner ring 40.
  • the inner ring 40 comprises two parts 45, 47, which are connected to one another in the region of the blade head 49 to form the groove 43.
  • a guide plate which, like the outer boundary wall 20 of the axial compressor 12 is usually formed of two ring segments, the flange connected at opposite ends and can be screwed.
  • the invention provides an annular flow channel 16 for an axial compressor 12, in which on the outer boundary wall 22 blades 36, 44 of two blade rings 32, 42 are attached.
  • the inner ring 40 is held by the blades 36 of the one ring and has such an axial extent that the blades 44 of the other of the two rings 42 each with radial gap formation opposite this.
EP11150590A 2011-01-11 2011-01-11 Ringförmiger Strömungskanal für einen Axialverdichter Withdrawn EP2474744A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11150590A EP2474744A1 (de) 2011-01-11 2011-01-11 Ringförmiger Strömungskanal für einen Axialverdichter
PCT/EP2011/071834 WO2012095220A1 (de) 2011-01-11 2011-12-06 Ringförmiger strömungskanal für einen axialverdichter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11150590A EP2474744A1 (de) 2011-01-11 2011-01-11 Ringförmiger Strömungskanal für einen Axialverdichter

Publications (1)

Publication Number Publication Date
EP2474744A1 true EP2474744A1 (de) 2012-07-11

Family

ID=44146305

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11150590A Withdrawn EP2474744A1 (de) 2011-01-11 2011-01-11 Ringförmiger Strömungskanal für einen Axialverdichter

Country Status (2)

Country Link
EP (1) EP2474744A1 (un)
WO (1) WO2012095220A1 (un)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012215412A1 (de) * 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
DE102012215413A1 (de) * 2012-08-30 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
EP2921715A1 (de) * 2014-03-20 2015-09-23 Rolls-Royce Deutschland Ltd & Co KG Schaufelreihengruppe
US9951635B2 (en) 2014-03-20 2018-04-24 Rolls-Royce Deutschland Ltd & Co Kg Group of blade rows

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014204346A1 (de) 2014-03-10 2015-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines doppelreihigen Schaufelrads für eine Strömungsmaschine und doppelreihiges Schaufelrad
DE102014205235A1 (de) * 2014-03-20 2015-09-24 Rolls-Royce Deutschland Ltd & Co Kg Schaufelreihengruppe

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB628263A (en) * 1943-06-01 1949-08-25 Louis Breguet Improvements in or relating to axial flow compressors
US2645413A (en) * 1947-04-16 1953-07-14 Rolls Royce Stator for multistage axial compressors
EP1111191B1 (en) * 1999-12-18 2006-03-22 General Electric Company Stator with particular circumferential spacing of the airfoils
US20070271924A1 (en) * 2006-05-29 2007-11-29 Snecma Device for guiding a stream of air entering a combustion chamber of a turbomachine
EP2194234A1 (de) 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Wärmeisolationsring zur passiven Spaltkontrolle in einer Gasturbine
EP2218876A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Dichtungsring zum Abdichten eines Radialspalts in einer Gasturbine
EP2261463A2 (de) * 2009-05-28 2010-12-15 Rolls-Royce Deutschland Ltd & Co KG Strömungsmaschine mit einer Schaufelreihengruppe

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB628263A (en) * 1943-06-01 1949-08-25 Louis Breguet Improvements in or relating to axial flow compressors
US2645413A (en) * 1947-04-16 1953-07-14 Rolls Royce Stator for multistage axial compressors
EP1111191B1 (en) * 1999-12-18 2006-03-22 General Electric Company Stator with particular circumferential spacing of the airfoils
US20070271924A1 (en) * 2006-05-29 2007-11-29 Snecma Device for guiding a stream of air entering a combustion chamber of a turbomachine
EP2194234A1 (de) 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Wärmeisolationsring zur passiven Spaltkontrolle in einer Gasturbine
EP2218876A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Dichtungsring zum Abdichten eines Radialspalts in einer Gasturbine
EP2261463A2 (de) * 2009-05-28 2010-12-15 Rolls-Royce Deutschland Ltd & Co KG Strömungsmaschine mit einer Schaufelreihengruppe

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012215412A1 (de) * 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
DE102012215413A1 (de) * 2012-08-30 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
US9366148B2 (en) 2012-08-30 2016-06-14 Rolls-Royce Deutschland Ltd & Co Kg Assembly of an axial turbomachine and method for manufacturing an assembly of this type
DE102012215413B4 (de) * 2012-08-30 2020-04-02 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
EP2921715A1 (de) * 2014-03-20 2015-09-23 Rolls-Royce Deutschland Ltd & Co KG Schaufelreihengruppe
US9951635B2 (en) 2014-03-20 2018-04-24 Rolls-Royce Deutschland Ltd & Co Kg Group of blade rows

Also Published As

Publication number Publication date
WO2012095220A1 (de) 2012-07-19

Similar Documents

Publication Publication Date Title
EP3056813B1 (de) Abdichtung eines randspalts zwischen effusionsschindeln einer gasturbinenbrennkammer
EP2960438B1 (de) Leitschaufelvorrichtung für eine gasturbine sowie gasturbine mit einer solchen leitschaufelvorrichtung
EP2148977B1 (de) Gasturbine
EP2824282A1 (de) Gasturbine mit Hochdruckturbinenkühlsystem
EP2474744A1 (de) Ringförmiger Strömungskanal für einen Axialverdichter
EP2873921A1 (de) Brennkammerhitzeabschirmelement einer Gasturbine
DE3700668C2 (de) Übergangskanaldichtvorrichtung
EP1789653A1 (de) Rotor f]r ein triebwerk
DE10318852A1 (de) Hauptgaskanal-Innendichtung einer Hochdruckturbine
EP3000984A1 (de) Leitschaufelverstellvorrichtung einer gasturbine
EP2921778A1 (de) Brennkammer einer Gasturbine
WO2003044329A1 (de) Gasturbogruppe
EP2730844A1 (de) Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
EP3095957B1 (de) Rotorscheibe zur verwendung in einem verdichter
EP2826958A1 (de) Rotor für eine thermische Strömungsmaschine
EP3287611A1 (de) Gasturbine und verfahren zum aufhängen eines turbinen-leitschaufelsegments einer gasturbine
EP2526263B1 (de) Gehäusesystem für eine axialströmungsmaschine
EP3236011A1 (de) Rotor mit überhang an laufschaufeln für ein sicherungselement
EP2358979B1 (de) Axialverdichter für eine gasturbine mit passiver radialspaltkontrolle
EP2394028B1 (de) Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine und ihre Verwendung
EP2955336B1 (de) Zwischengehäuse für eine Gasturbine sowie Gasturbine mit einem solchen Zwischengehäuse
EP2826957A1 (de) Rotor für eine thermische Strömungsmaschine
EP2980481A1 (de) Fluggasturbine mit einer dichtung zur abdichtung einer zündkerze an der brennkammerwand einer gasturbine
EP2725203B1 (de) Kühlluftführung in einer Gehäusestruktur einer Strömungsmaschine
DE112016006017B4 (de) Gasturbinenmotor

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20130112