EP3805642A1 - Refroidissement du cône pilote - Google Patents

Refroidissement du cône pilote Download PDF

Info

Publication number
EP3805642A1
EP3805642A1 EP19202651.6A EP19202651A EP3805642A1 EP 3805642 A1 EP3805642 A1 EP 3805642A1 EP 19202651 A EP19202651 A EP 19202651A EP 3805642 A1 EP3805642 A1 EP 3805642A1
Authority
EP
European Patent Office
Prior art keywords
pilot
burner
cooling air
cone
pilot cone
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Withdrawn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
EP19202651.6A
Other languages
German (de)
English (en)
Inventor
Christian Beck
Jürgen MEISL
Stefan Reich
Sabrina Isolde Siebelist
Christopher Grandt
Benjamin WITZEL
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 EP19202651.6A priority Critical patent/EP3805642A1/fr
Publication of EP3805642A1 publication Critical patent/EP3805642A1/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Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Definitions

  • the invention relates to a pilot cone for use in a burner arrangement, as well as a burner arrangement.
  • the invention also relates to a method for cooling a pilot cone of a burner arrangement.
  • Providing a central pilot burner with a cone for flame design is a widely used measure.
  • a pilot cone is cooled openly, ie the cooling air is fed to the combustion chamber after cooling and is mixed there with the flame. This is to be regarded as unfavorable in terms of reducing NO x emissions.
  • closed cooling with reuse of the cooling air is necessary.
  • the pilot cone In the case of closed cooling, the pilot cone is usually cooled by an integrated design with air, which is used as combustion air after the cooling task has been completed.
  • the cooling air is guided, for example, between a base plate facing the combustion chamber and an intermediate plate arranged on the back of the base plate, or between the pilot cone and the cooling cone arranged around the pilot cone, in order to cool the base plate or pilot cone and then take part in the combustion.
  • the object of the invention is to provide a pilot cone in which cooling air and scavenging air consumption are as small as possible and which is at the same time as simple and inexpensive to manufacture as possible.
  • Another object of the invention is to provide a burner arrangement with a pilot cone.
  • the invention solves the problem directed to a pilot cone by providing that in such a pilot cone for use in a burner arrangement with a pilot burner, the pilot cone having a jacket that widens downstream in a main flow direction of fuel and air, a cooling air duct for the Pilot cone runs in the jacket of the pilot cone.
  • pilot cone By utilizing the design options that additive manufacturing allows, it is possible to manufacture a pilot cone with integrated cooling.
  • the pilot cone is therefore a compact component that can be easily integrated into an existing burner and that enables a long service life.
  • the complexity of the cooling air routing is completely hidden inside the pilot cone and can only be produced using additive manufacturing methods.
  • the cooling air throughput is limited to the air throughput required for cooling, so that more air is available for premixing with the fuel.
  • annular gap is formed on the pilot cone by two circumferentially extending, upstream inclined, coaxial, radially inner and radially outer walls over which the air supplied to the pilot cone for cooling is distributed according to its use.
  • first openings in the radially inner wall and second openings between radially inner and radially outer wall are arranged in the jacket of the pilot cone, and the sum of the cross-sectional areas of all the first openings is greater than the sum of the cross-sectional areas of all the second openings.
  • the air supplied to the first and second openings has already been used to cool upstream components and the amount of cooling air has therefore been optimized primarily for the first use and typically exceeds the amount required for pilot cone cooling. With the selection of the size of the cross-sectional areas of the first and second openings, the amount of air that is not required for cooling the pilot cone can be separated off.
  • annular distributor is arranged in the jacket of the pilot cone, into which the second openings arranged in the circumferential direction open in order to distribute the cooling air evenly over the circumference of the pilot cone.
  • first cooling air passages branch off from the distributor and extend downstream within the jacket, and the first cooling air passages are connected via circumferentially oriented first transverse passages with directly adjacent, upstream extending second cooling air passages. This ensures efficient and even cooling in the pilot cone.
  • At least two first cooling air passages open into a first transverse passage and at least two second cooling air passages branch off from the first transverse passage.
  • the first and second cooling air passages are round in cross section. With rectangular cooling air passages, larger duct cross-sections can be realized, but round cooling air passages are more favorable in terms of material stresses and service life.
  • opening cross-sections of the second openings are smaller than cross-sections of the first and second cooling air passages or the first and second transverse passages.
  • the second openings which, as it were, represent the inlet openings into the cooling air duct in the pilot cone, are the smallest passages in the system and can intercept particles that could clog subsequent cooling channels. They are viewed as an integrated filter device. The number of the second openings therefore also exceeds the number of the first or second cooling air passages.
  • the inner surface of the jacket of the pilot cone i.e. the surface on the combustion chamber side
  • a thermal insulation layer as is generally the case.
  • the additive manufacturing method enables the simple addition of additional features. It can therefore be useful if at least three protruding prongs are arranged on the outside of the pilot cone as a catch protection. This safety catch keeps the pilot cone in the main burner in the unlikely event of an unintentional loosening of the pilot cone.
  • a burner arrangement comprising a main burner with a central opening along a main burner axis, a pilot burner arranged in the central opening and a direct burner downstream of the pilot burner and fluidically connected to this pilot cone.
  • pilot cone is attached to a support structure which carries the pilot burner and fluidically separates the pilot burner from the main burner.
  • the contact points between the pilot burner and the pilot cone are designed as sliding seats with leakage surfaces.
  • a sliding fit is a fit that can be easily joined, i.e. by hand or with light hammer blows.
  • a cooling air passage is formed by coaxially arranged support structures of the pilot burner or the pilot cone and the main burner, which opens into an annular gap in the pilot cone, the radially inner wall being the support structure of the pilot burner and the radially outer wall being the support structure of the main burner connects to the jacket of the pilot cone.
  • first openings in the radially inner wall lead into a chamber formed by the radially inner wall and the pilot burner, which is fluidically connected to an inlet of the pilot burner.
  • the amount of air required for cooling between the pilot and main burner can thus be divided into a part necessary for cooling the pilot cone and an excess part which is fed to the pilot burner for combustion.
  • the second cooling air passages open into an interface of the pilot cone with the pilot burner, on which a circumferential cavity is formed.
  • the cooling air of the pilot cone is thus used again after the pilot cone has been cooled to flush the interface between the pilot burner and the pilot cone. Otherwise air would have to be fed separately to this area.
  • the circumferential cavity is expediently formed by a recess in the pilot cone and its partial covering by the pilot burner.
  • sealing air outlets are arranged in the circumferential cavity equidistantly over the circumference, so that there is a uniform supply of sealing air in the area of the interface between the pilot cone and the pilot burner.
  • sealing air outlets i.e. sections of the second cooling air passages close to the outlet
  • sealing air outlets are inclined in such a way that they are inclined in the direction of a swirling pilot burner flow when the burner arrangement is in operation. This ensures that the flow is applied downstream of the circumferential cavity along the conical surface, or prevents it from becoming detached.
  • the outlet openings of the second cooling air passages are protected, for example, against soot particles in oil operation.
  • the object of the invention directed to a method is achieved by a method for cooling a pilot cone of a burner arrangement with a pilot burner, wherein the pilot cone comprises a jacket that widens downstream and is arranged immediately downstream of the pilot burner and is fluidically connected to it, in which cooling air is inside the Jacket is guided and the jacket leaving cooling air flushes an interface between the pilot burner and pilot cone.
  • Cooling air is advantageously supplied via a first cooling air passage and is returned via a second cooling air passage adjacent to the first cooling air passage.
  • First and second cooling air passages are connected to one another in the vicinity of the downstream end of the pilot burner via comparatively short first transverse passages.
  • the cooling air is the shortest route from the annular manifold at the upstream end to the vicinity of the downstream end of the pilot cone and returned from there by the shortest route. This results in an efficient and as uniform as possible cooling or temperature distribution in the pilot cone.
  • cooling air is returned via a second cooling air passage adjacent to the blocked second cooling air passage.
  • the complex internal channel structure is implemented using additive manufacturing; with conventional production it would be very difficult or impossible to produce.
  • the complexity which is seen as a cost driver in conventional manufacturing, causes additive manufacturing processes no extra charge.
  • the component can therefore be constructed very efficiently in terms of cooling performance and cooling air balance. Another advantage of additive manufacturing is the very short production times.
  • the Figure 1 shows schematically and by way of example a section of a burner arrangement 2, comprising a main burner 19 with a central opening 20 along a main burner axis 21, a pilot burner 3 arranged in the central opening 20 and a pilot cone 1 arranged directly downstream of the pilot burner 3 and connected to it in terms of flow technology between pilot burner 3 and pilot cone 1 are designed as sliding seats with leakage surfaces.
  • the pilot cone 1 is also attached to a support structure 22 which carries the pilot burner 3 and separates the pilot burner 3 from the main burner 19 in terms of flow.
  • the pilot cone 1 has a jacket 4 that widens downstream in a main flow direction of fuel and air.
  • An inner surface 16 of the jacket 4 of the pilot cone 1 is provided with a thermal insulation layer 17.
  • a cooling air duct 5 runs for the pilot cone 1 in the jacket 4 of the pilot cone 1.
  • the cooling air duct 5 refer to the Figures 3 to 5 referenced.
  • An outer cooling air passage 24 is formed by coaxially arranged support structures 22, 25 of the pilot burner 3 or of the pilot cone 1 and the main burner 19.
  • part of the pilot's combustion air (approx. 30-50%) is guided through this outer cooling air passage 24 to the pilot cone 1 in order to cool the support structure 25 of the main burner 19.
  • the outer passage 24 is optimized in order to generate the flow velocity necessary for the heat transfer with a low pressure loss at the same time.
  • the high pressure gradient between the cooling air inlet and outlet of the pilot cone 1 enables efficient cooling with a comparatively low air mass flow.
  • the outer cooling air passage 24 opens into an annular gap 6 of the pilot cone 1, which is formed by two upstream coaxial, radially inner and radially outer walls 7, 8 arranged on the jacket 4 and extending in the circumferential direction, the radially inner wall 7 being the support structure 22 of the pilot burner 3 and the radially outer wall 8 connects the support structure 25 of the main burner 19 to the jacket 4 of the pilot cone 1.
  • First openings 9 are arranged in the radially inner wall 7.
  • Second openings 10 are arranged between the radially inner 7 and radially outer wall 8 in the jacket 4 of the pilot cone 1.
  • the sum of the cross-sectional areas of all the first openings 9 is greater than the sum of the cross-sectional areas of all the second openings 10 to allow the main part of the cooling air from the outer cooling air passage 24 to be able to supply the pilot burner 3.
  • the first openings 9 in the radially inner wall 7 lead into a chamber 26 formed by the radially inner wall 7 and the pilot burner 3.
  • This chamber 26 is fluidically connected to an inlet 27 of the pilot burner 3.
  • FIGS Figure 2 shows the pilot cone 1 in a side view with inner 7 and outer wall 8. Furthermore, FIGS Figure 2 the areas of the pilot cone 1 indicated in the Figures 3 and 4th are described in more detail.
  • Figure 3 shows a section of the upstream cooling air duct 5 inside the pilot cone 1 and Figure 4 shows a section of the downstream cooling air duct 5.
  • the cooling air duct 5 can be adequately described, since the pattern of the cooling air duct 5 is repeated several times in the circumferential direction. The direction of view is always radially inwards.
  • annular distributor 11 is arranged, into which the second openings 10 arranged in the circumferential direction open.
  • the air for cooling the pilot cone 1 thus initially flows through a multiplicity of second openings 10, which are arranged in the circumferential direction, into the aforementioned annular distributor 11.
  • First cooling air passages 12 branch off from the distributor 11 and extend within the jacket 4 essentially downstream, but with a radial component due to the cone, being connected via circumferentially oriented first transverse passages 13 to directly adjacent, upstream second cooling air passages 14. The latter is in Figure 4 shown.
  • At least two first cooling air passages 12 open into a first transverse passage 13 and at least two second cooling air passages 14 branch off from the first transverse passage 13. Adjacent second cooling air passages 14 are connected to one another via second transverse passages 15. The first and second cooling air passages 12, 14 are round in cross section.
  • first cooling air passages 12 The air thus flows through the first cooling air passages 12 to the front edge of the pilot cone 1 and there flows via first transverse passages 13 to respectively adjacent second cooling air passages 14, which are provided for returning the air to the interface with the pilot burner 1.
  • the first and second cooling air passages 12, 14, ie the supply and return channels, are arranged alternately and adjacent second cooling air passages 14 are connected by second transverse passages 15 in order to allow, in the unlikely event of a blocked cooling passage, an albeit reduced cooling air flow through unblocked sections .
  • This emergency cooling property is intended to counteract further damage to the pilot cone 1 after damage with blocked cooling passages 12, 14, so that operation is possible until the end of the next service interval.
  • a damage scenario would be, for example, the melting of the front edge of the cone after the thermal insulation layer has flaked off and the cooling air passages 12, 14 are blocked.
  • Cross-sections of the second openings 10 are smaller than cross-sections of the first and second cooling air passages 12, 14 or the first and second transverse passages 13, 15 so that a filter function results at the entrance to the cooling air duct 5.
  • the second cooling air passages 14 open into an interface 28 of the pilot cone 1 with the pilot burner 3, ie after flowing through the pilot cone 1, the cooling air enters a circumferential cavity 29, the interface between the pilot cone 1 and the pilot burner 3, and mixes downstream with the pilot burner flow.
  • the circumferential cavity 29 is formed by the partial covering 31 of a recess 30 in the pilot cone 1 by the pilot burner 3 and is aerodynamically designed in such a way that the cooling air flows through or grazes potential dead water areas at the pilot burner outlet, so that there are no reaction zones of the fuel-air mixture of the pilot burner 3 can get stuck there and damage the structure through overheating.
  • sealing air outlets 32 are arranged equidistantly over the circumference in the circumferential cavity 29 and are oriented in such a way that, during operation of the burner arrangement 2, they are inclined in the direction of a swirling pilot burner flow, so that the flow is present downstream of the circumferential cavity 29 to ensure the conical surface or to avoid detachment.
  • the sealing air outlets 32 are protected, for example, against soot particles in oil operation.
  • the cooling is viewed as closed or cooling-air-neutral. Due to the high pressure gradient between the cooling air inlet and outlet, a high cooling effect is achieved with a low cooling air mass flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP19202651.6A 2019-10-11 2019-10-11 Refroidissement du cône pilote Withdrawn EP3805642A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19202651.6A EP3805642A1 (fr) 2019-10-11 2019-10-11 Refroidissement du cône pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19202651.6A EP3805642A1 (fr) 2019-10-11 2019-10-11 Refroidissement du cône pilote

Publications (1)

Publication Number Publication Date
EP3805642A1 true EP3805642A1 (fr) 2021-04-14

Family

ID=68280798

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19202651.6A Withdrawn EP3805642A1 (fr) 2019-10-11 2019-10-11 Refroidissement du cône pilote

Country Status (1)

Country Link
EP (1) EP3805642A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021228447A1 (fr) * 2020-05-15 2021-11-18 Siemens Aktiengesellschaft Refroidissement de cône de veilleuse
CN114215657A (zh) * 2021-12-01 2022-03-22 中国航发沈阳发动机研究所 一种航空发动机水冷中心锥
EP4113009A1 (fr) * 2021-06-28 2023-01-04 Delavan Inc Buses secondaires passives assistées par air

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1001221A2 (fr) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Structure de refroidissement pour une chambre de combustion d'une turbine à gaz
US20080000234A1 (en) * 2006-06-29 2008-01-03 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device
EP2256413A1 (fr) * 2009-05-27 2010-12-01 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement et procédé de montage
US20170292389A1 (en) * 2014-09-30 2017-10-12 Siemens Aktiengesellschaft Turbomachine component, particularly a gas turbine engine component, with a cooled wall and a method of manufacturing

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1001221A2 (fr) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Structure de refroidissement pour une chambre de combustion d'une turbine à gaz
US20080000234A1 (en) * 2006-06-29 2008-01-03 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device
EP2256413A1 (fr) * 2009-05-27 2010-12-01 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement et procédé de montage
US20170292389A1 (en) * 2014-09-30 2017-10-12 Siemens Aktiengesellschaft Turbomachine component, particularly a gas turbine engine component, with a cooled wall and a method of manufacturing

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021228447A1 (fr) * 2020-05-15 2021-11-18 Siemens Aktiengesellschaft Refroidissement de cône de veilleuse
US11971171B2 (en) 2020-05-15 2024-04-30 Siemens Energy Global GmbH & Co. KG Pilot cone cooling
EP4113009A1 (fr) * 2021-06-28 2023-01-04 Delavan Inc Buses secondaires passives assistées par air
US11859821B2 (en) 2021-06-28 2024-01-02 Collins Engine Nozzles, Inc. Passive secondary air assist nozzles
CN114215657A (zh) * 2021-12-01 2022-03-22 中国航发沈阳发动机研究所 一种航空发动机水冷中心锥
CN114215657B (zh) * 2021-12-01 2023-05-05 中国航发沈阳发动机研究所 一种航空发动机水冷中心锥

Similar Documents

Publication Publication Date Title
DE3908166B4 (de) Prallgekühltes Gebilde
EP2010773B1 (fr) Aube de turbine
DE69919298T2 (de) Kühlstruktur für eine Gasturbinenbrennkammer
EP3805642A1 (fr) Refroidissement du cône pilote
CH701774B1 (de) Monolithischer Brennstoffeinspritzkopf und zugehöriges Herstellungsverfahren.
EP2196734A1 (fr) Lance de combustible pour un brûleur
DE2844801A1 (de) Fluessigkeitsgekuehlter uebergangsteil und verfahren zu seiner herstellung
EP1005620A1 (fr) Element constitutif d'un bouclier thermique a recirculation du fluide de refroidissement
DE102004002888A1 (de) Gasturbinen-Endrohrdichtung und diese verwendende Gasturbine
DE102010016889A1 (de) System und Verfahren zum Kühlen der Wand einer Gasturbinenbrennkammer
DE112009000781T5 (de) Reparierbare Brennstoffdüse und Reparaturverfahren
EP2470834B1 (fr) Brûleur notamment destiné à des turbines à gaz
DE2617999A1 (de) Kuehlring fuer brennkammern
DE102009003347A1 (de) Verwirbelungsdüsenkonstruktion für eine Gasturbinenbrennkammer
EP2527743B1 (fr) Composant segmenté à base de matériau réfractaire pour une chambre de combustion annulaire, chambre de combustion annulaire pour un moteur d'aéronef, moteur d'aéronef et procédé de fabrication d'une chambre de combustion annulaire
EP2230458A1 (fr) Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
CH697703A2 (de) Kraftstoffdüsenanordnung.
DE102016104957A1 (de) Kühleinrichtung zur Kühlung von Plattformen eines Leitschaufelkranzes einer Gasturbine
DE3328682A1 (de) Brennerauskleidung fuer ein gasturbinentriebwerk
DE19801804C2 (de) Turbinenschaufel sowie Verfahren zur Inspektion und/oder Reinigung einer Turbinenschaufel
DE112014004655B4 (de) Brennstoffeinspritzvorrichtung für eine Gasturbine
EP3910238A1 (fr) Cône pilote
EP2069615A1 (fr) Élément filtrant destiné en particulier au filtrage des gaz d'échappement d'un moteur à combustion interne
EP3831498A1 (fr) Buse à faisceaux destinée à la pulvérisation d'un fluide, agencement doté d'une buse à faisceaux et procédé de fabrication d'une buse à faisceaux
EP1422479B1 (fr) Chambre pour la combustion d' un mélange combustible fluide

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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: 20211015