EP1635043A1 - Turbine avec une alimentation de gaz secondaire - Google Patents

Turbine avec une alimentation de gaz secondaire Download PDF

Info

Publication number
EP1635043A1
EP1635043A1 EP04021579A EP04021579A EP1635043A1 EP 1635043 A1 EP1635043 A1 EP 1635043A1 EP 04021579 A EP04021579 A EP 04021579A EP 04021579 A EP04021579 A EP 04021579A EP 1635043 A1 EP1635043 A1 EP 1635043A1
Authority
EP
European Patent Office
Prior art keywords
flow
secondary gas
turbine
gas stream
primary
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Withdrawn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
EP04021579A
Other languages
German (de)
English (en)
Inventor
Manuchehr Dr. Parvizinia
Heinrich Dr. Stüer
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 EP04021579A priority Critical patent/EP1635043A1/fr
Publication of EP1635043A1 publication Critical patent/EP1635043A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling

Definitions

  • the invention relates to a turbine with a turbine housing in which, during operation of the turbine, a primary gas flow can be conducted substantially in the direction of a longitudinal axis of the turbine, and a secondary gas supply, with a secondary gas flow can be introduced into the primary gas flow substantially transversely to the longitudinal axis.
  • gas is also understood to mean steam in a mono- or multiphase composition.
  • secondary gas streams In turbines, such as steam or gas turbines, it is customary to supply a main or primary gas stream further gas streams, so-called secondary gas streams.
  • secondary gas streams are secondary air, spent steam, vapor and steam, which is supplied to the cooling of the turbine components.
  • the secondary gas mass flow is less than 10% of the main gas mass flow.
  • partially decompressed steam is withdrawn from the housing of the turbine (e.g., after a medium pressure stage), which is then routed along the hot housing to receive seal leakage mass flows.
  • the extracted steam which for example has a temperature of about 200 ° C, also cools other components of the turbine and heats up to a temperature of about 400 ° C.
  • Such initiated secondary gas flow may essentially no additional pressure losses of the Cause main gas flow. Furthermore, when the secondary gas flow is introduced, no hot vapor layer may form over the adjacent components, such as, for example, housings and blades of the turbine. Cases in which the secondary gas flow is significantly hotter than the main gas flow and also only occasionally injected secondary gas, this represent a particular challenge to the design of the turbine.
  • the invention has for its object to provide a turbine with a turbine housing of the type mentioned, in which the above-mentioned difficulties overcome and in particular risks of hot gas stratification on adjacent components of Sekundärgaszu operationen are avoided.
  • the object is achieved in accordance with the invention with a generic turbine, in which a means for swirling the secondary gas flow into the primary gas flow is provided in the area of the introduction of the secondary gas flow into the primary gas flow. Furthermore, the object is achieved with a generic turbine in which a means for directing the secondary gas flow in the flow direction of the primary gas flow is provided in the region of the introduction of the secondary gas flow into the primary gas flow.
  • the invention is based on the finding that in order to avoid the abovementioned problems in the area of the introduction of the secondary gas flow into the primary gas flow, a homogeneous mixture of the partial flows with minimal pressure loss and at the same time a short mixing path has to be created.
  • a means is provided, by means of which a turbulence of the secondary gas flow into the primary gas flow into and thus a mixture of primary and secondary gas while avoiding hot gas layers is achieved.
  • Such mixing of the gas streams leads to a reduction in the risk of Layer flows and a rapid distribution of the supplied with the secondary gas energy flow.
  • the components in the immediate vicinity of the introduction of the secondary gas flow therefore undergo no increased temperature load according to the invention and can therefore be designed for a comparatively low temperature load. An over-dimensioning of the components only in the case of supplying particularly hot secondary gas can be avoided.
  • the invention proposes that the secondary gas stream is introduced with a flow-favorable injection geometry in the primary gas stream and is deflected specifically in the direction of the flow of the primary gas stream.
  • introduction of the secondary gas leads to the reduction of pressure losses and also promotes good mixing with the main gas stream.
  • the means for swirling and / or directing the secondary gas flow is formed with a arranged in the region of the introduction of the secondary gas flow on the housing flow area, which is overflowed by secondary gas flow edge at least partially wave-shaped.
  • the secondary gas flow is introduced into the primary gas flow in different sections of the flow path with different pressure gradients, whereby a strong vortex field is generated, which intensively mixes the partial flows due to the resulting transverse components.
  • a particularly strong mixing of the partial flows can also be advantageously provided with a flow surface as a means for swirling and / or steering, whose flow edge overflowed by the secondary gas flow is at least partially designed in a zig-zag shape.
  • the strongly zigzagging in the area of peaks narrowing Flow paths lead to a particularly strong vortex formation and to a correspondingly increased mixing of the said partial flows.
  • the particular non-linear flow edge of the steering device of the secondary gas flow according to the invention can be advantageously formed at least in sections in a plane which extends substantially in the axial direction of the turbine. With such a flow edge different amount of secondary gas is injected in the axial direction in the primary gas flow, whereby the said turbulence is promoted.
  • the wall of the housing of the thus designed turbine according to the invention can be made substantially smooth in the radial direction.
  • the flow edge may be formed at least in sections in a plane which extends substantially in the radial direction of the turbine.
  • Such a shape of a flow edge is particularly advantageous on a means for directing the secondary gas flow, which contributes to a very strong deflection towards the primary gas flow and thus parallel to the longitudinal axis of the turbine.
  • a further improvement of the solution according to the invention is achieved in that the means for swirling and / or steering is formed with a arranged in the region of the introduction of the secondary gas flow on the flow surface, which is movable into and out of the primary and / or secondary gas flow.
  • a flow area can, for example, during operation of the turbine according to the invention without secondary gas supply streamlined in the direction of the primary gas flow be aligned, while it moves in to inject the secondary gas stream in the primary gas flow and there leads to a turbulence and mixing of the two partial streams.
  • For the movement of the flow surface temperature characteristics can be specified, such that only as much mixing of the partial flows is achieved, as it is technically necessary. Flow losses can be minimized in this way.
  • the inventively movable flow area can be structurally particularly effective and at the same time comparatively inexpensive with a flexible hinged to the housing tab or hinged to the housing hinged flap.
  • a shape memory metal for moving the flow area, which changes its metal structure when it reaches a predetermined crystallization temperature and thereby assumes a predefined shape. This shape then determines the changed position of the flow area according to the invention.
  • the solution according to the invention a reduction of the flow losses during operation of a turbine with and without secondary gas supply, whereby a total of a higher efficiency is achieved.
  • the invention ensures a (in particular not convective only) thorough mixing of primary gas and secondary gas. This results in adjacent components a balanced temperature profile and the load on these components becomes more uniform.
  • the present invention achieved short mixing paths lead to the minimization of pressure losses and overall to improve the reliability.
  • the solution according to the invention can be realized inexpensively and with little structural modification effort. With the above developments, the solution can be adapted to a variety of applications and environmental situations.
  • a turbine 10 in the form of a steam turbine in longitudinal section is partially illustrated.
  • the turbine 10 has a shaft 12 which rotates about a longitudinal axis 14 during operation of the turbine 10.
  • On the shaft 12 are substantially radially extending blades 16 are mounted, of which one of a first medium-pressure stage or low-pressure stage 18 and a second of a second medium-pressure stage or low-pressure stage 20 are shown.
  • the rotor blades 16 are each associated with vanes 22, which likewise extend substantially radially and are attached to a substantially cylindrical housing 24 of the turbine 10.
  • a primary gas stream or primary steam stream 26 is passed during operation of the turbine 10, which can also be referred to as the main steam stream.
  • the primary gas flow 26 in this case flows essentially along the shaft 12 in the direction of the longitudinal axis 14 of the turbine 10.
  • a secondary gas stream 28 is fed to the turbine 10 between the medium-pressure stages or low pressure stages, which is supplied by a secondary gas supply 30 from the outside to the wall of the housing 24.
  • a means 32 for swirling and directing the secondary gas stream 28 when it enters the primary stream 26 is provided.
  • the means 32 deflects in particular the secondary gas stream 28 in the flow direction of the primary gas stream 26, so that in the region of the introduction of the secondary gas stream 28 particularly low pressure losses.
  • the means 32 leads to a turbulence of the secondary gas stream 28 in the inlet region and thus to a strong mixing of the partial streams. This strong mixing causes the comparatively hot secondary gas stream 28 relatively quickly in the primary gas stream 26 distributed and thereby increased temperature stress of the surrounding components is avoided.
  • the means 32 for this purpose has, in particular, a flow area which is partially overflowed by the secondary gas flow 28.
  • the flow area is designed in each case with a type of flap 34, which is articulated on the housing 24.
  • flap 34 tongues, tabs or so-called chevrons may be provided.
  • the flaps 34 each have a flow edge 36 on their peripheral region facing the secondary gas flow 28 or primary gas flow 26, which is designed to be wavy in the exemplary embodiment according to FIG. With such a waveform, different amounts of secondary gas are introduced into the primary gas flow 26 in sections in the axial direction as well as in the circumferential direction on the flap 34 in sections, which results in an increased turbulence of the partial flows.
  • the flow edge 36 is designed zigzag-shaped. With this comparatively pointed zig-zag shape, a particularly strong turbulence is achieved.
  • the flow edge 36 is finally of stepped design, the individual stages additionally being configured in each case with inclined flanks.
  • a deflection of the secondary gas flow 28 in the circumferential direction or a type of twist within the primary gas flow 26 is generated with the inclined flanks.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04021579A 2004-09-10 2004-09-10 Turbine avec une alimentation de gaz secondaire Withdrawn EP1635043A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04021579A EP1635043A1 (fr) 2004-09-10 2004-09-10 Turbine avec une alimentation de gaz secondaire

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04021579A EP1635043A1 (fr) 2004-09-10 2004-09-10 Turbine avec une alimentation de gaz secondaire

Publications (1)

Publication Number Publication Date
EP1635043A1 true EP1635043A1 (fr) 2006-03-15

Family

ID=34926493

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04021579A Withdrawn EP1635043A1 (fr) 2004-09-10 2004-09-10 Turbine avec une alimentation de gaz secondaire

Country Status (1)

Country Link
EP (1) EP1635043A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4835958A (en) * 1978-10-26 1989-06-06 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
EP0709550A1 (fr) * 1994-10-31 1996-05-01 General Electric Company Virole réfroidi
US6155778A (en) * 1998-12-30 2000-12-05 General Electric Company Recessed turbine shroud
US20020159880A1 (en) * 2001-04-26 2002-10-31 Honeywell International, Inc. Gas turbine disk cavity ingestion inhibitor
US20030035722A1 (en) * 2001-08-18 2003-02-20 Barrett David W. Gas turbine structure
US6553753B1 (en) * 1998-07-24 2003-04-29 General Electric Company Control systems and methods for water injection in a turbine engine
EP1496238A1 (fr) * 2003-07-09 2005-01-12 Snecma Moteurs Dispositif de réduction de bruit de jet d'une turbomachine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4835958A (en) * 1978-10-26 1989-06-06 Rice Ivan G Process for directing a combustion gas stream onto rotatable blades of a gas turbine
EP0709550A1 (fr) * 1994-10-31 1996-05-01 General Electric Company Virole réfroidi
US6553753B1 (en) * 1998-07-24 2003-04-29 General Electric Company Control systems and methods for water injection in a turbine engine
US6155778A (en) * 1998-12-30 2000-12-05 General Electric Company Recessed turbine shroud
US20020159880A1 (en) * 2001-04-26 2002-10-31 Honeywell International, Inc. Gas turbine disk cavity ingestion inhibitor
US20030035722A1 (en) * 2001-08-18 2003-02-20 Barrett David W. Gas turbine structure
EP1496238A1 (fr) * 2003-07-09 2005-01-12 Snecma Moteurs Dispositif de réduction de bruit de jet d'une turbomachine

Similar Documents

Publication Publication Date Title
DE102015201805B4 (de) Abgasturbolader
EP1505254B1 (fr) Turbine à gaz et méthode pour la refroidir
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
DE102004002888A1 (de) Gasturbinen-Endrohrdichtung und diese verwendende Gasturbine
DE102010037862A1 (de) Wirbelkammern zur Spaltströmungssteuerung
DE2454054A1 (de) Innentriebwerk bzw. gasgenerator fuer gasturbinentriebwerke
EP1653049B1 (fr) Couronne d'aubes directrices pour turbines à gaz et procédé pour sa modification
EP2092164B1 (fr) Turbo machine, en particulier turbine à gaz
EP3008292B1 (fr) Turbocompresseur à gaz d'échappement avec roue de turbine radiale-axiale
EP3179053B1 (fr) Structure de carter de turbomachine avec écran de protection thermique
EP2342425A1 (fr) Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
CH710576A2 (de) Turbinenschaufel mit mehreren Kühlkanälen.
DE102013002192A1 (de) Turbine für einen Abgasturbolader
EP3420199A1 (fr) Aube de turbine, dispositif associé, turbomachine et utilisation
DE102017110051A1 (de) Schaufel mit belastungsreduzierendem bauchigem Vorsprung an einer Wendeöffnung von Kühlmittelkanälen
CH714847B1 (de) Verschalung für einen Turbolader und Turbolader.
DE102018206601A1 (de) Schaufel, Schaufelsegment und Baugruppe für eine Turbomaschine und Turbomaschine
WO2010063575A1 (fr) Compresseur axial pour turbine à gaz, avec contrôle passif de la fente radiale
EP3312388A1 (fr) Pultdach dichtfin
EP1635043A1 (fr) Turbine avec une alimentation de gaz secondaire
EP3401503A1 (fr) Dispositif rotor d'une turbomachine
EP1423647B1 (fr) Dispositif a chambre de combustion
EP3551850B1 (fr) Procédé de modification d'une turbine
EP3587748B1 (fr) Structure de boîtier pour une turbomachine, turbomachine et procédé de refroidissement d'une section de boîtier d'une structure de boîtier d'une turbomachine
EP4166754A1 (fr) Ensemble rotor pour turbine à gaz avec surfaces de contact axiales inclinées formées sur des segments de rotor, turbine à gaz et turbine à gaz d'avion

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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

AKX Designation fees paid
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: 20060916

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566