EP2778531A1 - Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air - Google Patents

Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air Download PDF

Info

Publication number
EP2778531A1
EP2778531A1 EP13159017.6A EP13159017A EP2778531A1 EP 2778531 A1 EP2778531 A1 EP 2778531A1 EP 13159017 A EP13159017 A EP 13159017A EP 2778531 A1 EP2778531 A1 EP 2778531A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
air
section
connection space
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Withdrawn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
EP13159017.6A
Other languages
German (de)
English (en)
Inventor
Marco Link
Marc Tertilt
Martin Wilke
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP13159017.6A priority Critical patent/EP2778531A1/fr
Publication of EP2778531A1 publication Critical patent/EP2778531A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • the object of the invention is to remedy this.
  • a gas turbine is presented with a compressor for supplying a combustion chamber with compressed air, at least partially adjoining the combustion chamber terminal space, wherein from the connection space in the combustion chamber, air passages are formed, which serve for cooling.
  • a compressor for supplying a combustion chamber with compressed air, at least partially adjoining the combustion chamber terminal space, wherein from the connection space in the combustion chamber, air passages are formed, which serve for cooling.
  • Such a construction is common in gas turbines.
  • a higher pressure prevails in the terminal compartment than in the combustion chamber. Due to the pressure difference flows through the air passages air.
  • a cooling of the combustion chamber wall ie the wall between the connection space and the combustion chamber is achieved. This is due to both the lower temperature of the air and the fact that the flow causes flames in the combustion chamber to be kept away from the combustion chamber wall.
  • a device is provided with which the flow cross section for air flowing from the compressor into the connection space can be changed.
  • the change in the flow cross-section leads to a change in the flow resistance and thus the pressure in the connection space.
  • the changed pressure in the connection space leads to a changed flow of cooling air through the air outlets into the combustion chamber.
  • the device increases the flow cross-section for the air flowing from the compressor into the connection space, the flow resistance decreases.
  • the air gets easier in the terminal compartment, where the pressure increases.
  • more cooling air flows through the air passages in the combustion chamber.
  • less air coming from the compressor is available, which flows directly into a combustion region of the combustion chamber.
  • this is desirable since otherwise the combustion temperature would drop due to a reduced fuel supply.
  • a decreasing combustion temperature would lead to increased CO emissions.
  • a decrease in the so-called primary zone temperature below 1400 ° C leads to increased CO emissions.
  • the invention thus allows an extended power range at the expense of a low efficiency loss.
  • the electricity market also demands flexible power plants due to the increasing use of renewable energies.
  • the invention is equally useful in a sole operation of the gas turbine as in combined operation, in which from the waste heat of the gas turbine steam is still provided for a steam turbine.
  • connection space between the combustion chamber and an outer housing of the gas turbine wherein the terminal space is limited in particular by a combustion chamber outer shell. This corresponds to a proven construction of a gas turbine.
  • the combustion chamber is an annular combustion chamber. This can be achieved particularly well that the combustion chamber wall is cooled by the cooling air, while in the combustion zone prevails a desired high temperature.
  • the device with which the flow cross-section can be influenced can be an orifice and / or a flap and / or an arrangement of several orifices and / or flaps.
  • a flap or aperture is easy to implement and allows easy and safe influencing of the flow cross-section.
  • a slider an array of perforated plates in which the holes are aligned for a high flow area and are not aligned for a low flow area, and various known or easily developed further components and arrangements are conceivable.
  • such an air path exists from the compressor into the connection space that sufficient air can flow into the connection space when adjusting the device that supplies the minimum flow cross section, so that during operation a sufficient air flow for cooling can be set from the connection space into the combustion chamber ,
  • This can work with closed panels or flaps, for example, without jeopardizing the necessary cooling.
  • the cooling requirements of here featured gas turbine corresponds to the cooling demand of a conventional gas turbine in the art.
  • the air passages are formed so that when setting the device that provides minimum flow cross section, enough air for cooling from the terminal compartment can flow into the combustion chamber. For example, it is possible to provide more air outlets or larger air outlets than is usual in the prior art. Thus, even with a setting of the device that provides minimal flow cross-section, that is about closed flaps, enough cooling air available, even if it is difficult because of closed flaps of air into the connection space.
  • the device can be used to set the flow cross section as a function of a fuel flow supplied to the combustion chamber and / or of a power of the gas turbine and / or of a CO value.
  • the CO value can be detected in the exhaust gas flowing out of the combustion chamber. Since it is about avoiding a too high CO value, the approach is certainly to capture the CO value and increase the flow cross-section with increased CO value, a sensible way.
  • other approaches make sense, such as a control of the device as a function of the amount of fuel supplied or the power of the gas turbine.
  • One approach is also the change in the flow cross-section as a function of the combustion temperature. Of course, this presupposes the not always easy detection of this temperature.
  • control unit which is designed to control the device accordingly. It should be emphasized that the control unit can be designed for the approaches described above, but also for a variety of other approaches that are conceivable within the scope of the present invention.
  • the device is arranged in the region in which the cross section between the outer housing and the combustion chamber is minimal. This can be well influenced with relatively little effort, the flow cross-section.
  • the invention also relates to a method for operating a gas turbine with a compressor and a combustion chamber, wherein the flow cross-section is set for by the compressor in a space provided for cooling the combustion chamber and so the amount of cooling air is changed.
  • FIG. 1 a gas turbine burner 1 can be seen on the top left.
  • the main stream of compressed air is passed through the burner 1 in an annular combustion chamber 2 to burn a fuel there.
  • a portion of the compressed air can flow through the surrounding space 3 into a connection space 4. It can be seen that at the in FIG. 1 shown position of a flap 5 only a restricted flow cross-section is available. Therefore, the flow resistance is comparatively high, so that only a comparatively limited pressure is established in the connection space 4.
  • connection space 4 is sufficient to allow sufficient cooling air to flow through a combustion chamber wall 6, which surrounds the annular combustion chamber 2 and delimits the combustion chamber to the connection space 4 as the combustion chamber outer shell. More specifically, the cooling air flows through the schematically shown air passages 7 in the FIG. 1 are two Air diffusers shown schematically. In fact, a plurality of such air outlets 7 is present.
  • FIG. 2 corresponds to FIG. 1 ,
  • This is a much larger flow cross-section for the flow from the ambient space 3 in the connection space 4 available. Thanks to the lower flow resistance, a higher pressure builds up in the connection space 4. Accordingly, more cooling air flows into the annular combustion chamber 2 through the air passages 7. As a result, less air flows directly into the annular combustion chamber 2 through the burners 1. As described, this increases the fuel-air ratio during combustion. In partial load operation, in which the fuel supply is limited, thus a reduction of the combustion temperature and concomitantly an increase in CO emissions can be avoided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP13159017.6A 2013-03-13 2013-03-13 Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air Withdrawn EP2778531A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13159017.6A EP2778531A1 (fr) 2013-03-13 2013-03-13 Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13159017.6A EP2778531A1 (fr) 2013-03-13 2013-03-13 Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air

Publications (1)

Publication Number Publication Date
EP2778531A1 true EP2778531A1 (fr) 2014-09-17

Family

ID=47877904

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13159017.6A Withdrawn EP2778531A1 (fr) 2013-03-13 2013-03-13 Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air

Country Status (1)

Country Link
EP (1) EP2778531A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4008958A1 (fr) 2020-12-07 2022-06-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion de turbine à gaz et procédé de fonctionnement d'un système de chambre de combustion de turbine à gaz
EP4664012A1 (fr) 2024-06-12 2025-12-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Agencement de chambre de combustion et procédé de fonctionnement d'un agencement de chambre de combustion

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1257610A (fr) * 1967-11-10 1971-12-22
FR2133832A1 (fr) * 1971-04-15 1972-12-01 United Aircraft Canada
US3952501A (en) * 1971-04-15 1976-04-27 United Aircraft Of Canada Limited Gas turbine control
GB2277582A (en) * 1993-04-29 1994-11-02 Snecma Combustion chamber with a variable oxidant injection system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1257610A (fr) * 1967-11-10 1971-12-22
FR2133832A1 (fr) * 1971-04-15 1972-12-01 United Aircraft Canada
US3952501A (en) * 1971-04-15 1976-04-27 United Aircraft Of Canada Limited Gas turbine control
GB2277582A (en) * 1993-04-29 1994-11-02 Snecma Combustion chamber with a variable oxidant injection system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4008958A1 (fr) 2020-12-07 2022-06-08 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion de turbine à gaz et procédé de fonctionnement d'un système de chambre de combustion de turbine à gaz
DE102020132494A1 (de) 2020-12-07 2022-06-09 Deutsches Zentrum für Luft- und Raumfahrt e.V. Gasturbinenbrennkammersystem und Verfahren zum Betreiben eines Gasturbinenbrennkammersystems
EP4664012A1 (fr) 2024-06-12 2025-12-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Agencement de chambre de combustion et procédé de fonctionnement d'un agencement de chambre de combustion

Similar Documents

Publication Publication Date Title
EP2831394B1 (fr) Turbine à gaz avec système d'air de refroidissement réglable
DE112016000551B4 (de) Kühlsystem für eine gasturbine, damit versehene gasturbinenausstattung und teile-kühlverfahren für eine gasturbine
EP3186498B1 (fr) Ensemble de turbine à gaz
DE102014117621A1 (de) Brennstoffinjektor mit Vormisch-Pilotdüse
CH699760A2 (de) Brennstoffdüse mit einem Brennstoff-Luft-Vormischer für eine Gasturbinenbrennkammer.
DE102015120448A1 (de) Vormischbrennstoffdüsenanordnung
DE112013007579B4 (de) Flüssigbrennstoffpatrone für eine Brennstoffdüse und Brennstoffdüse
CH710574B1 (de) System und Verfahren zur Nutzung von Kühlluft in einem Brenner.
DE102009003759A1 (de) Steuerungssysteme und Verfahren zum Steuern eines Lastpunktes einer Gasturbine
CH703587B1 (de) Druckbetätigter Stopfen.
CH701773B1 (de) Brenner mit einem Einlassleitschaufelsystem.
EP2676023B1 (fr) Procédé de refroidissement d'un étage de turbine
DE102020212410A1 (de) Gasturbinenverbrennungsvorrichtung
EP2023041A1 (fr) Brûleur à prémélange et procédé de mise en oeuvre du brûleur
EP3132202B1 (fr) Element de bouclier thermique avec contournement
CH707753A2 (de) Turbinenanordnung und Verfahren zur Lieferung einer Spülluftströmung und einer einstellbaren Kühlluftströmung zu einem Hohlraum in einer Gasturbine.
DE102015119749A1 (de) Vormischbrennstoffdüsenanordnung
EP2071156B1 (fr) Système de distribution de carburant d'une turbine à gaz avec ensemble brûleur à plusieurs étages
WO2012016748A2 (fr) Chambre de combustion de turbine à gaz
DE102005042889A1 (de) Gasturbogruppe
EP2778531A1 (fr) Turbine à gaz avec combustion optimisée en charge partielle par réglage du débit d'air
EP1934523B1 (fr) Chambre de combustion et turbine à gaz
DE102016115580A1 (de) System und Verfahren zur Einhaltung von Emissionsgrenzwerten während des Betriebs einer Gasturbine bei Teillastbetriebszuständen
DE970711C (de) Gasturbinenanlage zur Erzeugung heisser Druckluft
CH707917A2 (de) Lufterhitzungssystem mit katalytischer Verbrennung.

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

17P Request for examination filed

Effective date: 20130313

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

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: 20150318