WO2014111325A1 - Procédé de régulation d'un flux massique de gaz, canal d'écoulement et turbomachine munie dudit canal d'écoulement - Google Patents

Procédé de régulation d'un flux massique de gaz, canal d'écoulement et turbomachine munie dudit canal d'écoulement Download PDF

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Publication number
WO2014111325A1
WO2014111325A1 PCT/EP2014/050435 EP2014050435W WO2014111325A1 WO 2014111325 A1 WO2014111325 A1 WO 2014111325A1 EP 2014050435 W EP2014050435 W EP 2014050435W WO 2014111325 A1 WO2014111325 A1 WO 2014111325A1
Authority
WO
WIPO (PCT)
Prior art keywords
flow channel
flow
turbomachine
gas mass
flow duct
Prior art date
Application number
PCT/EP2014/050435
Other languages
German (de)
English (en)
Inventor
Francois Benkler
Stefan Braun
Stephan Klumpp
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2014111325A1 publication Critical patent/WO2014111325A1/fr

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Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0065—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid
    • F15D1/0075—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid comprising electromagnetic or electrostatic means for influencing the state of the fluid, e.g. for ionising the fluid or for generating a plasma
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • F05D2270/172—Purpose of the control system to control boundary layer by a plasma generator, e.g. control of ignition

Definitions

  • the present invention relates to a method for Steue ⁇ tion of flowing through a flow channel gas mass flow and a flow channel, which is designed to carry out this method and a turbomachine with this flow channel.
  • a flow channel is present, for example, as a diffuser or inlet in a turbomachine, such as a gas turbine. Through the flow channel flows during operation of the door ⁇ bomaschine a gas mass flow.
  • the activation of the plasma actuator takes place according to a predefined scheme.
  • a control of the activation of the plasma actuators can take place after a precalculation.
  • the activation of the plasma actuators is then dependent on the geometry of the flow channel when specific characteristics rela ⁇ hung as if he achieves certain characteristic value combinations. These characteristics can include the rotor speed, the amount of air, the temperature or simply the time.
  • the control is preferably carried out by a control unit.
  • the activation of the plasma Actuator when falling below a certain speed of the gas mass flow is determined in particular by means of sensors in the flow channel.
  • the flow conduit according to the invention with a limit it ⁇ the wall according to the invention comprises at least one disposed on the Wan ⁇ dung and / or at a positioned in the flow channel guide profile plasma actuator.
  • the plasma actuators are preferably connected to a control unit.
  • the flow channel according to the invention advantageously provides a flow channel with which a gas mass flow can be influenced.
  • the flow channel according to the invention requires for influencing no moving parts. It is relatively easy and inexpensive to manufacture.
  • the individual components for the flow channel according to the invention are very easy to design. Plasma actuators are thin, flexible and can be simply glued on, for example.
  • the flow channel according to the invention can be designed shorter in its axial length than conventional flow channels who ⁇ . Turbines can thus be made cheaper.
  • the flow channel according to the invention offers the possibility ⁇ ability to be retrofitted in existing turbomachinery can.
  • this has a plurality of plasma actuators, which are arranged radially to an axis of rotation.
  • the velocity of the gas masses ⁇ stream close to the wall can be influenced by the disposed on the walls of plasma actuators in a given cross section of the flow channel ⁇ the entire circumference. That offers the opportunity, ever upon request, to generate swirling effects or to counteract a swirl of the gas mass flow.
  • the radially arranged plasma actuators are activated circumferentially.
  • a simultaneous activation of the plasma actuators is possible.
  • this has a plurality of plasma Aktuato ⁇ ren, which are arranged along the flow channel.
  • the gas mass flow can be accompanied influencing in its course.
  • On one point of the flowing gas mass flow can be acted several times. This point happens successively the several arranged in the longitudinal direction
  • Plasma actuators In particular, a combination of radially and longitudinally arranged plasma actuators provides extensive opportunities for influencing.
  • the inventive flow channel of the flow channel is a diffuser and the wall of the flow channel is formed from a Gehotkon ⁇ tur and a hub contour.
  • At least one plasma actuator is arranged on the housing contour and / or on the hub contour and / or in the guide profile.
  • turbomachines can be increased by preventing an early stall.
  • the flow channel according to the invention designed as a diffuser allows this possibility.
  • the flow channel is an inlet of a turbine.
  • the design of the flow channel according to the invention as an inlet additionally offers the possibility of optimizing a turbomachine.
  • the through the inlet to the turbine flowing air can be influenced according to the requirements by means of the plasma actuators and thus a more efficient, resource-saving operation of the turbine can be obtained.
  • the flow channel according to the invention is preferably integrated in a turbomachine.
  • the turbomachine is in particular a gas turbine.
  • the advantages of the flow channel according to the invention thus benefit the turbomachine as an assembly.
  • FIG. 1 shows a turbomachine according to the invention with a
  • FIG. 1 shows the turbomachine with the flow channel with
  • a turbomachine 1 according to the invention is shown by way of example.
  • the turbomachine 1 is in particular a gas turbine.
  • the turbomachine 1 shown here has a compressor 2 and a diffuser 3.
  • the diffuser 3 is madebil ⁇ det as inventive flow channel 17.
  • the diffuser 3 is integrally ⁇ classified here downstream of the compressor. 2
  • the diffuser 3 may also be a diffuser, which is arranged downstream of a turbine of a turbomachine 1.
  • the flow channel 17 according to the invention can also be an inlet of a turbine of the turbomachine 1.
  • the compressor 2 comprises a plurality of rows of blades 4, which are fixed to a rotor and a plurality of rows with Guide vanes 5, which are fastened to a housing 14.
  • the rotor blades 4 rotate with the rotor about an axis of rotation 15.
  • a row with outlet blades 6 is positioned, which in particular are adjustable.
  • the turbomachine 1 according to the invention has at least be ⁇ rich manner the flow channel 17 according to the invention.
  • the flow channel 17 according to the invention can be positio ⁇ ned in the diffuser 3 and / or in the inlet of the turbine of the turbomachine 1 and / or elsewhere.
  • a gas mass flow 9, 10 flows through the flow channel 17.
  • the flow channel 17 according to the invention is formed by the diffuser 3.
  • the diffuser 3 is positioned adjacent to the compressor 2 downstream of the compressor 2.
  • a wall of the flow channel 17 is in this case formed by a hub 16 and the housing 14.
  • the cross section of the flow channel 17 extends downstream ⁇ Windbook towards an outlet. 13
  • the diffuser 3 reduces ⁇ with the speed of the gas mass flow 9, 10th
  • the diffuser 3 which is formed by the flow channel 17 according to the invention, may for example be a diffuser 3 for an annular combustion chamber or for a silo combustion chamber.
  • the flow channel 17 has at least one plasma actuator 7. This can be arranged on the wall of the flow channel 17 or on a guide channel 8 positioned in the flow channel, a so-called strut.
  • the flow channel 17 has a plurality of plasma actuators 7.
  • the wall of the flow channel 17 is in this case formed by the hub 16 and the housing 14.
  • the flow channel 17 points in This way, therefore, an annular cross-section.
  • the plasma actuators 7 may be positioned on both the hub 16 and the housing 14.
  • the plasma actuators 7 may be arranged on the at least one guide profile 8.
  • an arrangement of the plasma actuators 7 is provided extending in the flow direction or also in radial rows.
  • the plasma actuators 7 positioned one behind the other in the flow direction can influence the gas mass flow 9, 10 over a region along the flow direction.
  • the radially arranged plasma actuators 7 can provide for influencing an entire edge region of the cross section.
  • Plasma actuators 7 to generate an additional twist. Depending on the application, it is possible in the other direction to reduce the possible swirl of the gas mass flow 9, 10 by activating the radially arranged plasma actuators 7 in succession opposite the direction of rotation of the rotor.
  • FIG. 1 shows the flow channel 17 according to the invention, acting here as a diffuser 3, in a first situation in which the plasma actuators 7 are not activated.
  • FIG. 2 shows the flow channel 17 according to the invention in a second situation, in which the plasma actuators 7 are activated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Plasma & Fusion (AREA)
  • Fluid Mechanics (AREA)
  • Plasma Technology (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un procédé permettant de réguler un flux massique de gaz (9, 10) parcourant un canal d'écoulement (17) d'une turbomachine (1). Le procédé consiste à activer au moins un actionneur plasma (7) agencé dans le canal d'écoulement (17), de sorte que le flux massique de gaz (9, 10) est au moins en partie accéléré. L'invention concerne par ailleurs un canal d'écoulement (17) et une turbomachine (1) munie dudit canal d'écoulement (17).
PCT/EP2014/050435 2013-01-15 2014-01-13 Procédé de régulation d'un flux massique de gaz, canal d'écoulement et turbomachine munie dudit canal d'écoulement WO2014111325A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013200470.2 2013-01-15
DE201310200470 DE102013200470A1 (de) 2013-01-15 2013-01-15 Verfahren zur Steuerung eines Gasmassenstroms, Strömungskanal sowie Turbomaschine mit Strömungskanal

Publications (1)

Publication Number Publication Date
WO2014111325A1 true WO2014111325A1 (fr) 2014-07-24

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/050435 WO2014111325A1 (fr) 2013-01-15 2014-01-13 Procédé de régulation d'un flux massique de gaz, canal d'écoulement et turbomachine munie dudit canal d'écoulement

Country Status (2)

Country Link
DE (1) DE102013200470A1 (fr)
WO (1) WO2014111325A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017110333A1 (de) * 2017-05-12 2018-11-15 Airbus Operations Gmbh Fluidtransportsystem für ein Luftfahrzeug

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070241229A1 (en) * 2006-04-12 2007-10-18 The Boeing Company Inlet distortion and recovery control system
EP1928216A1 (fr) * 2006-11-29 2008-06-04 Lockheed Martin Corporation Contrôle de flux électromagnétique d'entrée
EP2128388A2 (fr) * 2008-05-30 2009-12-02 Honeywell International Inc. Diffuseur
US20100122536A1 (en) * 2008-11-17 2010-05-20 Honeywell International Inc. Plasma flow controlled diffuser system
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation
US20110048025A1 (en) * 2009-08-26 2011-03-03 Lockheed Martin Corporation Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070241229A1 (en) * 2006-04-12 2007-10-18 The Boeing Company Inlet distortion and recovery control system
EP1928216A1 (fr) * 2006-11-29 2008-06-04 Lockheed Martin Corporation Contrôle de flux électromagnétique d'entrée
EP2128388A2 (fr) * 2008-05-30 2009-12-02 Honeywell International Inc. Diffuseur
US20100122536A1 (en) * 2008-11-17 2010-05-20 Honeywell International Inc. Plasma flow controlled diffuser system
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation
US20110048025A1 (en) * 2009-08-26 2011-03-03 Lockheed Martin Corporation Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators

Also Published As

Publication number Publication date
DE102013200470A1 (de) 2014-07-17

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