EP3889506A1 - Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant - Google Patents

Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant Download PDF

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Publication number
EP3889506A1
EP3889506A1 EP20167166.6A EP20167166A EP3889506A1 EP 3889506 A1 EP3889506 A1 EP 3889506A1 EP 20167166 A EP20167166 A EP 20167166A EP 3889506 A1 EP3889506 A1 EP 3889506A1
Authority
EP
European Patent Office
Prior art keywords
burner
vortex generator
burner component
wall section
maximum
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Withdrawn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
EP20167166.6A
Other languages
German (de)
English (en)
Inventor
Ramsatish KALURI
Stefan Dederichs
Michael Huth
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 EP20167166.6A priority Critical patent/EP3889506A1/fr
Priority to PCT/EP2020/085563 priority patent/WO2021197654A1/fr
Priority to US17/909,408 priority patent/US20230151966A1/en
Priority to EP20828979.3A priority patent/EP4078032A1/fr
Priority to CN202080099239.2A priority patent/CN115362333B/zh
Priority to KR1020227037339A priority patent/KR20220153655A/ko
Publication of EP3889506A1 publication Critical patent/EP3889506A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex

Definitions

  • the invention relates to a burner component of a burner for use in a gas turbine.
  • the task of the burner component considered here is to bring about or promote swirling of combustion air with fuel.
  • disruptive elements are usually arranged in the flow path, which deflect the flow and thereby cause a swirl.
  • Blade-like structures are often used for this.
  • the flow resistance is important to be kept as low as possible and still ensure adequate mixing.
  • the object of the present invention is therefore to bring about improved mixing with the lowest possible resistance.
  • the generic burner component is intended to be a component of a burner.
  • the type of burner involved is initially irrelevant, but the burner component is advantageously used in a burner of a gas turbine. It is obvious here that the burner is to be arranged on the upstream side of a combustion chamber.
  • the burner has a flow channel in which combustion air flows in a flow direction from upstream to downstream.
  • the flow channel is necessarily limited by a wall.
  • the burner component now comprises, at least in sections, the wall adjoining the flow channel as a wall section.
  • a plurality of injection nozzles are generically arranged on the wall section. How the fuel is supplied to the injection nozzles is initially irrelevant. At least the injection nozzles are provided to enable fuel to be introduced into the flow channel. Consequently, the injection nozzles are initially connected to a fuel channel regardless of how it is designed or arranged.
  • the vortex generators are each arranged on the wall section and protrude into the flow channel.
  • the vortex generators as an obstacle in the flow channel, cause the combustion air to swirl.
  • the vortex generators have a shape with a starting edge running on the wall section.
  • the starting edge represents the boundary of the vortex generator on the upstream side.
  • the starting edge can have both an arcuate and a straight course.
  • the starting edge here runs along (not necessarily exactly in) a transverse direction which is oriented transversely to the flow direction on the wall section or tangentially to the wall section.
  • a terminating edge is located on the downstream side of the respective vortex generator.
  • the terminating edge extends in each case along (not necessarily exactly in) a vertical direction. This is aligned transversely to the wall section and transversely to the direction of flow.
  • the end of the terminating edge on the wall section forms a base point, with an end point located opposite at the terminating edge.
  • the respective vortex generator is limited on the one hand by two oppositely arranged side surfaces.
  • the side surfaces starting from the terminating edge, run upstream towards the opposite edge ends of the starting edge.
  • the vortex generator is limited by an inclined surface, which begins at the starting edge and runs to the end point.
  • the incline surface is delimited laterally, at least in sections, by the side surfaces.
  • the vortex generator has a vortex generator length which is measured in the direction of flow and extends from the starting edge to the base point. If the starting edge does not extend in a straight line in the transverse direction, so the point to be chosen on the starting edge is that which is located furthest upstream. This point can be the center, but in the case of a wall section that is not even, it will usually be an edge of the starting edge.
  • the inclined surface is now designed to be concave. This means that the incline surface is a curved surface that is deeply shaped into the vortex generator.
  • the vortex generators in the embodiment considered here have an approximately triangular shape. This applies both when viewed in the direction of flow and in the vertical direction with a view of the slope surface. Likewise, a view in the transverse direction shows the respective side surface with an approximately triangular shape.
  • a curvature has been shown to be advantageous in terms of improving the intermixing with the modification of a planar plane to a concave inclined surface, which has a certain deviation from a planar slope plane.
  • the slope plane is defined here by the end point and two further points of the circumferential edge of the slope surface, so that the slope surface lies completely below the slope plane.
  • a maximum distance between the inclined surface and the inclined plane of at least 0.03 times the vortex generator length and a maximum of 0.3 times the vortex generator length is preferred.
  • a maximum distance of at least 0.06 times the vortex generator length is particularly advantageous. Furthermore, it is particularly advantageous if the maximum distance corresponds to a maximum of 0.2 times the vortex generator length.
  • the side surfaces show a convex curvature in a section through the vortex generator along a plane transverse to the vertical direction.
  • the respective side surfaces form, in the simplest form, a section of a cylindrical surface.
  • An advantageous mixing of fuel in the combustion air is achieved if at least one injection nozzle is arranged in the immediate area of influence of the vortex generator.
  • an injection nozzle can advantageously be arranged on at least one side of the vortex generator in a side surface of the vortex generator or in the immediately adjacent wall section at a distance from the base of a maximum of 0.4 times the vortex generator length. It is particularly preferred here if the distance of the injection nozzles (regardless of the arrangement in the side surface or the wall section) to the base point corresponds to a maximum of 0.3 times the vortex generator length. Furthermore, an injection nozzle can advantageously be arranged on both sides of the vortex generator.
  • the injection nozzles are arranged in the center of the respective vortex generator.
  • an advantageous mixing of the fuel in the combustion air is brought about downstream of the vortex generator.
  • the injection nozzles are arranged directly on the vortex generator at the terminating edge (the injection nozzle interrupts the terminating edge or reduces its length at the base).
  • the injection nozzles can be arranged downstream of the vortex generator in the wall section.
  • the distance from the injection nozzle to the base point corresponds to a maximum of 0.4 times the vortex generator length. It is particularly advantageous if the distance corresponds to a maximum of 0.3 times the vortex generator length. In this way, the advantageous influence of the vortex generator with the concave incline surface is optimally used to achieve the best possible mixing of the fuel in the combustion air.
  • the injection nozzle when arranged on the wall section, is arranged at a distance from the base of at least 0.1 times the vortex generator length.
  • a further advantageous introduction of the fuel into the combustion air is made possible when at least one injection nozzle is arranged between two vortex generators. It is particularly advantageous to have precisely one injection nozzle in the middle between arranged the vortex generators.
  • the relevant arrangement relates to the position in the transverse direction.
  • the at least one injection nozzle between the vortex generators is also positioned in spatial proximity to the base point when viewed in the direction of flow. It is advantageous if the distance from the base point to the injection nozzle also corresponds to a maximum of 0.3 times the vortex generator length. It has been shown to be particularly preferred if the injection nozzle is arranged downstream of the base point at a maximum distance of 0.2 times the vortex generator length.
  • the multiple vortex generators can be arranged next to one another and offset from one another in the direction of flow.
  • the vortex generators are preferably arranged next to one another at the same height in the direction of flow. In this regard, it is unimportant whether other means for swirling the air flow are arranged upstream or downstream outside the immediate area of influence of the vortex generator.
  • the vortex generators are arranged at a distance from one another in the transverse direction.
  • the vortex generators are directly adjacent to one another. It is particularly advantageous here if, due to the adjoining arrangement of the vortex generators, the respective adjacent inclined surfaces have a common edge section.
  • the burner component as part of a burner can fulfill different functions.
  • the burner component can form a pipe section which surrounds the flow channel.
  • the burner component can form a section of a wall of the flow channel, with two or more sections, for example each as a burner component, surrounding the flow channel.
  • the burner component is intended to adjoin the flow channel suggests mixing fuel in combustion air in accordance with the intended task.
  • the burner component forms a burner lance.
  • the burner lance has a wall in the form of a rotation, with which the flow channel surrounds the wall section of the burner component.
  • the vortex generators are arranged distributed around the circumference of the wall section, the vortex generators being designed as described above.
  • a burner component according to the invention leads to the formation of a burner according to the invention which is used as intended on a combustion chamber.
  • the burner in a combustion chamber of a gas turbine is particularly advantageous, the burner component also preferably being a burner lance.
  • the burner comprises at least one mixing tube which surrounds the flow channel and is arranged upstream of the combustion chamber.
  • the burner component used here, with a design as described above, is arranged centrally in the mixing tube.
  • the use of the burner component according to the invention in a mixing tube brings about an advantageous mixing of fuel in the combustion air and thus enables largely pollutant-free combustion.
  • FIG. 1 is shown in a perspective view of an exemplary embodiment for a burner component 01 according to the invention in the form of a burner lance.
  • the typical rotationally shaped, elongated shape of the burner lance 01 can be seen.
  • the slightly conical wall of the burner lance forms the wall section 03 of the burner component 01 as a delimiting surface for the flow channel intended for use in the burner. This correspondingly defines the flow direction 05 from an upstream side to a downstream side.
  • the arrangement of a plurality of vortex generators 11 distributed around the circumference can also be seen, each of which has an approximately triangular shape when viewed from different directions.
  • the arrangement of several injection nozzles 21, 22, which are arranged downstream of the vortex generators 11, can also be seen.
  • the respective vortex generator 11 is delimited upstream by a starting edge 14.
  • the starting edge 14 runs along a transverse direction which is perpendicular to the direction of flow and tangential to the wall section 03. Due to the arrangement of the vortex generators 11 on the rotationally shaped wall section 03, the starting edge 14 is curved, so that the two opposite edge ends 15 of the starting edge 14 are arranged furthest upstream.
  • the vortex generator 11 is delimited by the terminating edge 16, which extends approximately in a respective vertical direction from a base point 18 on the wall section 03 to an end point 17. The vertical direction is aligned approximately perpendicular to the flow direction and perpendicular to the wall section 03 at the base point 18.
  • the distance from the terminating edge 16 to the edge ends 15 measured in the flow direction 05 defines a vortex generator length.
  • the respective vortex generator 11 is laterally bounded by two opposite side surfaces 19 which each extend from the terminating edge in the direction of the respective edge end 15 of the starting edge 14. As can be seen, the side surfaces 19 have a curved, convex shape.
  • the surface of the vortex generator which is essential for the swirling of the fuel in the combustion air, forms the inclined surface 12, which extends from the starting edge 14 to the end point 17.
  • the inclined surface 12 is delimited in sections by cutting edges with the two side surfaces 19.
  • the vortex generators 11 are arranged adjacent to one another in such a way that a common Edge portion of the adjacent incline surfaces 12 starting from the respective edge end 15 to essentially the beginning of the side surfaces 19 results.
  • the inclined surface 12 has a convexly curved shape. This is the decisive feature for achieving the advantageous turbulence and thus a further possibility for reducing pollutants during combustion.
  • the incline surface 12 is located below a theoretical incline plane 13.
  • the incline plane 13 is defined by the end point 17 and the two edge ends 15, so that the incline surface 12 is arranged completely below the incline plane 13.
  • the maximum distance between the incline surface 12 and the theoretical incline plane 13 corresponds to 0.1 times the vortex generator length.
  • injection nozzles 21, 22 can also be seen from the views.
  • an injection nozzle 21 is located in the wall section 03 in the center behind a vortex generator 11.
  • the distance from the center of the respective injection nozzle 21 to the base point 18 of the terminating edge 16 is approximately 0.2 times the vortex generator length in this exemplary embodiment.
  • a further injection nozzle 22 is arranged on the wall section 03 between two vortex generators 11.
  • the distance from the center of the injection nozzle 22 to the foot point 18 of the vortex generator 11 is approximately 0.16 times the vortex generator length.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP20167166.6A 2020-03-31 2020-03-31 Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant Withdrawn EP3889506A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP20167166.6A EP3889506A1 (fr) 2020-03-31 2020-03-31 Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant
PCT/EP2020/085563 WO2021197654A1 (fr) 2020-03-31 2020-12-10 Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type
US17/909,408 US20230151966A1 (en) 2020-03-31 2020-12-10 Burner component of a burner, and burner of a gas turbine having a burner component of this type
EP20828979.3A EP4078032A1 (fr) 2020-03-31 2020-12-10 Composant de brûleur d'un brûleur, et brûleur d'une turbine à gaz présentant un composant de brûleur de ce type
CN202080099239.2A CN115362333B (zh) 2020-03-31 2020-12-10 燃烧器的燃烧器部件和燃气轮机的具有这种燃烧器部件的燃烧器
KR1020227037339A KR20220153655A (ko) 2020-03-31 2020-12-10 버너의 버너 구성요소 및 이러한 유형의 버너 구성요소를 갖는 가스 터빈의 버너

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20167166.6A EP3889506A1 (fr) 2020-03-31 2020-03-31 Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant

Publications (1)

Publication Number Publication Date
EP3889506A1 true EP3889506A1 (fr) 2021-10-06

Family

ID=70110124

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20167166.6A Withdrawn EP3889506A1 (fr) 2020-03-31 2020-03-31 Composant de brûleur d'un brûleur et brûleur d'une turbine à gaz doté d'un tel composant

Country Status (1)

Country Link
EP (1) EP3889506A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3578264A (en) * 1968-07-09 1971-05-11 Battelle Development Corp Boundary layer control of flow separation and heat exchange
US4260367A (en) * 1978-12-11 1981-04-07 United Technologies Corporation Fuel nozzle for burner construction
EP0619457A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Brûleur à prémélange
EP0694740A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Chambre de combustion
EP0775869A2 (fr) * 1995-11-23 1997-05-28 Abb Research Ltd. Brûleur à prémélange
WO2015150114A1 (fr) * 2014-04-03 2015-10-08 Siemens Aktiengesellschaft Brûleur, turbine à gaz munie dudit brûleur et injecteur de combustible

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3578264A (en) * 1968-07-09 1971-05-11 Battelle Development Corp Boundary layer control of flow separation and heat exchange
US3578264B1 (fr) * 1968-07-09 1991-11-19 Univ Michigan
US4260367A (en) * 1978-12-11 1981-04-07 United Technologies Corporation Fuel nozzle for burner construction
EP0619457A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Brûleur à prémélange
EP0694740A2 (fr) * 1994-07-25 1996-01-31 Abb Research Ltd. Chambre de combustion
EP0775869A2 (fr) * 1995-11-23 1997-05-28 Abb Research Ltd. Brûleur à prémélange
WO2015150114A1 (fr) * 2014-04-03 2015-10-08 Siemens Aktiengesellschaft Brûleur, turbine à gaz munie dudit brûleur et injecteur de combustible

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