EP2407673A1 - Compresseur - Google Patents

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Publication number
EP2407673A1
EP2407673A1 EP10007156A EP10007156A EP2407673A1 EP 2407673 A1 EP2407673 A1 EP 2407673A1 EP 10007156 A EP10007156 A EP 10007156A EP 10007156 A EP10007156 A EP 10007156A EP 2407673 A1 EP2407673 A1 EP 2407673A1
Authority
EP
European Patent Office
Prior art keywords
compressor
pin
housing
vane
flow channel
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Withdrawn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
EP10007156A
Other languages
German (de)
English (en)
Inventor
Thomas Brandenburg
Daniel Ecke
Markus Hofmann
Markus Kunze
Torsten Matthias
Bernward Dr. Mertens
Dirk MÜLLER
Markus Paus
Andre Placzek
Jens Sander
Achim Schirrmacher
Vadim Shevchenko
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 EP10007156A priority Critical patent/EP2407673A1/fr
Publication of EP2407673A1 publication Critical patent/EP2407673A1/fr
Withdrawn legal-status Critical Current

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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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the invention relates to a compressor with an annular flow channel radially outwardly bounding housing in which are supported radially rotatably supported by the flow channel extending vanes of a vane ring.
  • variable inlet guide vanes comprise an airfoil disposed on a circular plate.
  • the plate forms the platform of the compressor blade.
  • a pin is provided at the back of the plate.
  • the pin serves as a drive shaft for rotating the inlet guide vane of the compressor about its longitudinal axis.
  • To accommodate the pin bores are provided in the housing of the compressor, which lie for each vane ring in a plane perpendicular to the machine axis of the axial compressor and each extending in the radial direction, based on the machine axis.
  • the pins penetrate the holes, so that a lever is attached to the outside of the housing on each pin, with which the rotational movement of the compressor blade can be effected.
  • a so-called adjusting ring is articulated to the levers, whereby a rotational movement of the adjusting ring in the circumferential direction is converted into a rotation of the pin about its longitudinal axis.
  • freestanding vanes as adjustable vanes.
  • the object of the invention is therefore to provide a reliable compressor with adjustable vanes whose disassembly and installation time are shortened in case of maintenance.
  • a compressor having an annular flow channel radially outwardly delimiting housing in which are radially mounted rotatably supported by the flow channel extending vanes of a vane ring, wherein provided for rotation of each vane extending through the housing pin is, whose first end is connected to the vane, wherein the connection between the vane and the respective pin is releasable.
  • the invention is based on the finding that, if the guide blade and pin are not integrally formed, but are detachable from each other, the airfoil including platform through the flow channel of the compressor can be removed, without having to lift the upper housing part of the compressor. After removal of the guide vane the associated pin remains in its bore.
  • This type of disassembly of the adjustable vane saves significant installation effort, which significantly reduces the downtime of the compressor or a gas turbine equipped with such a compressor.
  • Another great advantage is that the vane is only one side, that is mounted on the housing side and thus has a defined radial position. The freestanding blade tip opposite wall of the rotor then serves exclusively to the inner boundary of the annular flow channel and is thus no longer required for receiving hub-side guide blade pins, which otherwise not freestanding vanes were stored in an inner ring.
  • the relevant vane has a platform on the housing side, which is connected by a cone connection with the pin.
  • a transversely extending aerodynamically curved blade is disposed on a first side of the platform and a truncated cone on a second side facing away from the blade, which truncated cone is clamped in a arranged at the first end of the pin conical receptacle.
  • the use of a cone connection ensures that the airfoil of the vane is arranged in concentric extension of the journal axis. It is thus specified a centric connection, which avoids any assembly-related incorrect or inclined positions of the blade against the pin axis as far as possible.
  • the cone connection is preferred.
  • the pin extends longitudinally through the respective pin screwed into the truncated cone clamping screw.
  • the pin is thus formed as a hollow shaft.
  • the clamping screw in this case has a screw head, which can be supported on the second end of the pin, whereby the clamping of the clamping screw of the truncated cone is drawn into the conical receptacle of the pin.
  • an adjustable bearing unit is provided on the housing, which supports the respective pin.
  • the adjustable bearing unit can of course also be used if the guide blade and pin are not designed modular, but monolithic. Due to the adjustable bearing unit, the gap between the inner boundary wall of the annular channel and the blade tip can be adjusted to the desired level. The brushing of the blade tip on the rotor can thus be avoided. If the airfoil has a profile which projects beyond the platform edge, the housing-side radial gap between projecting airfoil and housing can be adjusted simultaneously with the adjustable bearing unit.
  • the platforms of the vanes are each sunk to an annular, with respect to the flow channel surface corresponding recessed Anaptungs Solutions sunk.
  • This allows a nearly continuous and edge-free flow path boundary surface, which is very wind-slippery. Aerodynamic losses can thus be largely avoided.
  • connection with the respective pin is solvable in all guide vanes.
  • the rotatable vanes are formed as free-standing vanes, so that when releasing the connection between the pin and the guide vane these need only be slightly tilted to remove them from their operating position.
  • a simple removal of the rotatable vanes is particularly possible if they are formed as inlet guide vanes of the compressor. In this case, no further blades are arranged upstream of the inlet guide vanes, which facilitates access for a fitter.
  • a stationary gas turbine expediently has a compressor of the aforementioned type.
  • the single figure shows a longitudinal section through a section of an axial compressor.
  • the single figure shows a longitudinal section through an axial type compressor 10, in the section of its inlet guide vanes 12 rotatable about its respective longitudinal axis 52.
  • the illustrated inlet guide vane 12 is representative of any variable length vanes 14 of a compressor 10.
  • the compressor 10 includes both an axial one as well as circumferentially divided housing 16.
  • the housing 16 surrounds the machine axis 18 of the compressor 10, along which an annular flow channel 20 extends. Radially outward, the inwardly facing surface 22 of the housing 16 defines the flow channel 20. Radially inward, the flow channel 20 is bounded by the outer circumferential surface 24 of a compressor rotor 26.
  • the compressor rotor 26 is rotatable about the machine axis 18.
  • the guide blade 14 is formed without a head-side platform, so that its free-standing blade tip 30 of the lateral surface 24 is radially gap forming opposite.
  • a circular platform 32 is provided in the form of a plate, wherein platform 32 and blade 28 form a monolithic unit.
  • the platform comprises on its side facing away from the airfoil 28 side 34 a truncated cone 36.
  • a pin 38 At the truncated cone 36 is a pin 38 with its first end 40 at. Is to at the first end 40, a conical receptacle 41 (cone) provided on the front side.
  • the pin 38 extends through a bore 42 arranged in the housing 16, so that the second end 44 of the pin 38 projects out of the housing 16.
  • a lever 46 is arranged, to which an adjusting ring, not shown, is articulated.
  • the pin 38 is hollow, so that a clamping screw 48 extends through it.
  • the clamping screw 48 has a screw head 50, which is supported on the second end 44 of the pin 38.
  • the clamping screw 48 is simultaneously screwed into a provided in the truncated cone 36 threaded hole 49, whereby the truncated cone 36 is seated biased in the arranged at the first end 40 conical receptacle 41.
  • the pin 38 is rotatably mounted in the bore 42, so that the pin 38 and attached thereto the guide vane 14 about the common longitudinal axis 52 are uniformly rotatable or pivotable.
  • an adjustable bearing unit 54 is provided for the pin 38, with its radial position and thus also the radial position of the guide vane 14 can be specified. It is a fixed bearing with radial adjustment.
  • the platform 32 is recessed on a reflection surface 35 in the form of a floating bearing 56.
  • the platform 32 including truncated cone 36 instead of the threaded hole 49 has a through hole through which the clamping screw 48 extends.
  • the clamping screw 48 is then screwed into a threaded hole arranged on the blade 28, so that both the pin 38 and the platform 32 are clamped between the screw head 50 and the blade 28.
  • the platform 32 does not necessarily have a circular shape. Other contours are also possible.
  • a compressor 10 is provided with adjustable guide vanes 14, in which the airfoil 28 of the vane 14 through the flow channel 20 to the compressor 10 can be removed.
  • the pin 38 required in the housing 16 for the rotatable mounting of the guide blade 14 be detachable from the blade leaf 28.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10007156A 2010-07-12 2010-07-12 Compresseur Withdrawn EP2407673A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10007156A EP2407673A1 (fr) 2010-07-12 2010-07-12 Compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10007156A EP2407673A1 (fr) 2010-07-12 2010-07-12 Compresseur

Publications (1)

Publication Number Publication Date
EP2407673A1 true EP2407673A1 (fr) 2012-01-18

Family

ID=43244794

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10007156A Withdrawn EP2407673A1 (fr) 2010-07-12 2010-07-12 Compresseur

Country Status (1)

Country Link
EP (1) EP2407673A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2980366A1 (fr) * 2014-07-30 2016-02-03 MTU Aero Engines GmbH Boitier pour une turbine a gaz, groupe motopropulseur et procede de fonctionnement d'une turbine a gaz
US20200182082A1 (en) * 2018-12-10 2020-06-11 United Technologies Corporation Modular variable vane assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040240990A1 (en) * 2003-05-27 2004-12-02 Rockley Christopher I. Variable vane arrangement for a turbomachine
EP1818509A1 (fr) * 2006-02-09 2007-08-15 Siemens Aktiengesellschaft Agencement d'aubes de guidage
EP1892422A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Aubes de guidage pour compresseur et méthode pour les remplacer dans le compresseur

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040240990A1 (en) * 2003-05-27 2004-12-02 Rockley Christopher I. Variable vane arrangement for a turbomachine
EP1818509A1 (fr) * 2006-02-09 2007-08-15 Siemens Aktiengesellschaft Agencement d'aubes de guidage
EP1892422A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Aubes de guidage pour compresseur et méthode pour les remplacer dans le compresseur

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2980366A1 (fr) * 2014-07-30 2016-02-03 MTU Aero Engines GmbH Boitier pour une turbine a gaz, groupe motopropulseur et procede de fonctionnement d'une turbine a gaz
US9988927B2 (en) 2014-07-30 2018-06-05 MTU Aero Engines AG Housing for a gas turbine, aircraft engine, and a process for operating a gas turbine
US20200182082A1 (en) * 2018-12-10 2020-06-11 United Technologies Corporation Modular variable vane assembly
EP3667030A1 (fr) * 2018-12-10 2020-06-17 United Technologies Corporation Ensemble d'aube variable modulaire pour un compressuer d'un moteur à turbine à gaz
US10830087B2 (en) * 2018-12-10 2020-11-10 Raytheon Technologies Corporation Modular variable vane assembly

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