EP2784393A1 - Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire - Google Patents

Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire Download PDF

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Publication number
EP2784393A1
EP2784393A1 EP13160969.5A EP13160969A EP2784393A1 EP 2784393 A1 EP2784393 A1 EP 2784393A1 EP 13160969 A EP13160969 A EP 13160969A EP 2784393 A1 EP2784393 A1 EP 2784393A1
Authority
EP
European Patent Office
Prior art keywords
flaps
combustion system
combustion chamber
combustion
flap
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Withdrawn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
EP13160969.5A
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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
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 EP13160969.5A priority Critical patent/EP2784393A1/fr
Priority to PCT/EP2014/053382 priority patent/WO2014154401A1/fr
Publication of EP2784393A1 publication Critical patent/EP2784393A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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

Definitions

  • the invention relates to a combustion system that can be operated in partial load operation CO emissions compliant.
  • the combustion temperature drops in the combustion chamber.
  • the primary zone temperature relevant for CO emissions also falls below a minimum value. Due to the resulting increased CO emissions, the usable partial load range of the gas turbine is limited. In this case, if a legal CO emission limit exists, the operator of a gas turbine may be forced to shut down his gas turbine if it is not possible for him to further reduce the output of his gas turbine without simultaneously exceeding the CO emission limit.
  • the object of the invention is therefore to further develop the combustion system of a gas turbine, so that the gas turbine can be operated in the partial load range CO emission compliant.
  • the flaps are connected via rotatable connections with the support structure of the outer shell, wherein the rotatable connections are oriented in the circumferential direction of the combustion chamber.
  • the redirected amount of air can be well metered and mix in the lowest possible disturbance flowing in the direction of the turbine combustion gases in the combustion chamber.
  • the combustion chamber comprises heat shield plates whose size substantially corresponds to the size of the flaps and inner sides of the flaps are provided with ceramic heat shield plates.
  • the flaps are arranged distributed substantially uniformly over a circumference of the combustion chamber.
  • a stop of the flaps on the compressor side and in each case a circumferential collar between the outside of the flaps and support structure allows opening of the flaps only in the direction of the combustion chamber interior.
  • a stop of the flaps on the turbine side and in each case a circumferential collar between the inside of the flaps and support structure allows the flaps to open only to the outside.
  • a flow channel is formed, via which the air stream taken from the compressor end flows into the combustion chamber.
  • the channel is such that an angle ⁇ 90 ° is formed between the main flow of the combustion chamber and the secondary air flow. This ensures that no hot gas can flow into the gap between the flap and adjacent heat shield plates and that the support structure of the outer shell is not thermally stressed (e.g., by scaling).
  • the fail-safe position of the flaps is the flap-closed position.
  • the flaps are pressed against the surrounding collar in the supporting structure. This is z. B. by a sufficiently strong leaf spring package on the stop side of the flaps or torsion springs with permanent restoring force ensured at the tilting bearing of the flaps.
  • the mechanism remains in the "closed position" and is not undesirably printed by the pressure difference between the combustion chamber interior and the outer plenum.
  • the contact pressure on the support structure by the springs should be selected so that no pressure drops below a minimum contact pressure for each pressure difference occurring during operation of the gas turbine.
  • the force required to open the flap is chosen so that it can be applied via the opening mechanism provided for this purpose.
  • a mechanical adjusting device for adjusting an opening width of the flaps is provided.
  • This can be relatively easily realized with a cam which is arranged on a shaft and rests against a flap. Depending on the angle of rotation, the cam has a different radius in the direction of the flap and, with a corresponding rotation, can press on the flap against which it bears continuously.
  • a contact surface for the mechanical adjusting device is provided in a turbine-side region on the cold gas side of the flaps, in particular if in the region of this contact surface a bearing block, for example a graphite block or a block of a hard alloy on cobalt Chromium-based, is provided, whereby the sliding properties of the surface of the contact surface, in particular in the present in the combustion system temperatures are improved.
  • the cam is connected to a drive shaft with length compensation by a sliding seat, whose one end passed through an outer shell surrounding the outer shell of the combustion chamber and there in a fixed bearing secured against axial displacement.
  • a gas turbine can now be operated in the partial load range CO emissions compliant.
  • the combustion system according to the invention could also be used to improve combustion stability by setting more fat or lean mixtures as needed.
  • FIG. 1 shows schematically and by way of example an embodiment of an arranged between the compressor 25 and turbine 26 combustion system 1 according to the invention with a combustion chamber 2, comprising an outer shell 3 with a support structure 4.
  • the combustion chamber 2 has a compressor-side 5 and a turbine-side end 6. At the compressor end 5 is in Operation via burner 7, a fuel and air from the compressor 25 of the combustion chamber 2 and burned in the combustion chamber 2. The hot combustion gases are passed through the turbine end 6 of the combustion chamber 2 in the turbine 26.
  • a part 36 of the air from the compressor 25 is not passed through the burners 7 but past them via flaps 8 in the outer shell 3 into the combustion chamber 2 ( FIGS. 4, 5 . 8th . 11, 12 . 14 . 17 and 18 ).
  • the opening width of the flaps 8 is regulated depending on the occurring CO emissions. By this measure, the Combustion temperature in the combustion chamber 2 always kept so high that the relevant for CO emissions primary zone temperature does not fall below a minimum value.
  • the amount of the redirected air mass flow is determined via a "CO map" stored in a controller and / or the measurement of the current CO emissions.
  • a CO emission sensor 27 can be arranged at the turbine-side end 6 of the combustion chamber 2 or at the inlet of the turbine 26.
  • the flaps 8 are opened by a stepless mechanical adjustment 17 different widths. Due to the gap width that forms, there is a variable area through which the amount of bypassed air mass flow can be regulated.
  • the size of the flaps 8 is based on the dimensions of a ceramic heat shield plate 10. To lower the temperature profile before the turbine 26 as evenly as possible, the flaps 8 should be evenly distributed around the circumference of the combustion chamber 2, for example, four to twelve flaps 8 in the upper - And four to twelve in the lower part of the combustion chamber outer shell 3.
  • the flaps 8 in the FIG. 1 are designed so that an opening takes place in the direction of the combustion chamber space.
  • the flaps 8 are attached to the support structure 4 of the combustion chamber outer shell 3 and are in the embodiment of the FIG. 1 in the fourth row of stones 28 (when using the flaps 8 in silo separation chambers in the lower section of the flame tube).
  • another row of stones would be conceivable, for example, the third row of stones 29th
  • flap 8 is located on the compressor side, wherein the flap 8 is connected via a rotatable connection 9, for example a bolt, with the support structure 4.
  • a rotatable connection 9 for example a bolt
  • a sliding block or system block for example a graphite block, can be used.
  • a cam 18 which is arranged on a shaft 30.
  • the shaft 30 is rotatably mounted by two bearings 35 (one in front of the valve construction, one behind).
  • the bearings 35 are firmly connected to the combustion chamber outer shell 4 z. B. welded. Between the bearings 35 with the shaft 30 positively connected cam 18 is arranged.
  • the rotational movement of the shaft 30 is converted via the cam 18 in a translational movement.
  • the translation is achieved by the cam 18 by a rotation of z. B. 90 ° a radius R1 evenly extended to a larger radius R2 (s. Figures 3 and 5 ).
  • This translational movement is transmitted via the end face 31 of the cam 18 and via the contact surface 19 on the flap 8, which is thereby pressed into the combustion chamber 2.
  • the flap 8 can be opened differently wide.
  • FIG. 2 does not show is that the contact surface 19 and the cam 18 can also be firmly connected to each other, for. B. by a bolt on the flap 8, which runs in a slot on the cam 18. Thus, both a compressive and tensile force can be transmitted to the flap 8.
  • the fail-safe position of the flap 8 ie the position at which it comes to the least possible damage in the event of a fault, is the flap-closed position.
  • This is z. B. ensured by a sufficiently strong leaf spring package 16 on the abutment side of the flap 8 or torsion springs with permanent restoring force on the tilting bearing of the flap 8 (s. Figures 2 and 4 ).
  • the mechanism remains in the "closed position" and is not pressed by the pressure difference between annular combustion chamber interior and outer plenum 32 undesirable.
  • the contact pressure on the support structure 4 by the springs 16 is to be chosen so that at each pressure difference occurring during operation of the gas turbine, a minimum contact pressure is not exceeded. Furthermore, the force required to open the flap 8 is selected such that it can be applied via the mechanical adjusting device 17.
  • the torque transmission takes place by a propeller shaft 20 with length compensation by a sliding seat 33 to compensate for the heat expansion-related relative movement of the combustion chamber 2 relative to the outer housing 21.
  • One end of the propeller shaft 20 is guided through the outer housing 21 of the machine to the outside.
  • the shaft 20 is secured in a fixed bearing 22 against axial displacement. In addition to storage, the shaft passage is sealed. A rotational movement of the shaft 20 by e.g. 90 ° is possible.
  • a corresponding device is provided on the outer shaft end, z. B. a lever 34 for rotating or a shaft-hub connection for connecting an actuator.
  • a flap 8 is actuated by the articulated shaft 20 described from outside the machine and the tilting movement of this one flap 8 is transmitted via the push rod connections 23 to all other flaps 8.
  • FIG. 8 shows an alternative embodiment of the invention, in which on the outside of the flap 8 in the turbine 26 closer located area a mounting option for an actuator 24 is provided, for. B. a T-groove 37 for receiving a T-shoe 38 ( FIG. 10 ) or an eyelet for connecting the actuator 24 via a suitable bolt connection.
  • the opening of the flap 8 is achieved by the actuator 24 extends and thus pushes the turbine 26 next part of the flap 8 in the direction of the combustion chamber interior. This is in the FIGS. 9 to 12 shown.
  • the flap 8 By fixing the flap 8 on the side facing the compressor, it is also here to form a circumferential gap between the flap 8 and adjacent support structure 4, through the secondary air, so bypassed compressor air 36 can flow into the combustion chamber 2.
  • the gap is wedge-shaped on the sides of the flap 8, rectangular at the downstream edge.
  • the actuators 24 are connected via corresponding devices 39 fixed to the outer shell 3 of the annular combustion chamber 2. By occurring during operation of the gas turbine thermal expansion and the associated relative movement of the outer shell 3 to the outer housing 21, the actuator 24 remains in the defined position on the flap mechanism.
  • the actuators 24 used as drives eg water-cooled or air-cooled water-hydraulic, oil-hydraulic or pneumatically actuated cylinders with spring return 45 (fail-safe position: cylinder retracted, flap closed) are placed so firmly over the combustion chamber outer shell that is pushed by extending the piston, the turbine-side portion of the flap inward and the flap 8 thus opens ,
  • FIG. 13 shows an actuator 24 in a highly simplified representation.
  • the drive is encapsulated air or water tight 40 and is protected by a continuously flowing medium 41, eg air or water, from overheating.
  • the piston 42 of the cylinder is made of a low temperature conductive material and is dimensioned so that the part of the piston, which is exposed to high temperatures during retraction, does not come in contact with the interior of the cylinder, but in front of the actual cylinder housing in the cooled Encapsulation 40 is cooled down.
  • connections or lines for inlet 43 and outlet 44 at the cylinders are also actively cooled, z. B. by double-walled lines, which are flowed through in the outer duct by a continuously flowing medium circuit.
  • the conduits 46 are secured to the grommet positions on the outer housing 21 via flanged connections.
  • the pipes form inside the gas turbine one or more ring lines 47 which are fixedly connected to the housing.
  • the ring lines 47 are designed at least in two parts with a pitch in the area of the housing joint and are mounted by releasable connections (eg screw connection with cap screws).
  • releasable connections eg screw connection with cap screws.
  • the lines 48 such as flexible temperature-resistant hoses or rigid pipes with saucedehnungskompensatoren are connected via detachable connections to the actuators 24 and the loop 47. For inspection or maintenance purposes, a disassembly of the lines 48 is possible.
  • the control of the piston 42 is ideally carried out continuously and individually for each piston 42, but can also be simplified via a pure end position control (flap to / on) and a bundling of the piston by means of ring line.
  • FIG. 14 shows a further embodiment of the invention, in which the turbine 26 closer side of the flap 8 via a rotatable connection 9, for example a bolt, is connected to the support structure 4.
  • a rotatable connection 9 for example a bolt
  • Flap 8 and support structure 4 are on the inside of the flap 8 via a peripheral collar 14 at. Opening the flap 8 is only possible to the outside through this circumferential contact surface. The opening of the flap 8 is achieved by the actuator 24 retracts and thus the closer to the compressor 25 part of the flap 8 is lifted from the outer shell 3. By fixing the flap 8 on the turbine side, it comes to the rotational movement of the flap 8 to the fixed point and to form a circumferential gap between the flap 8 and support structure 4, can flow through the secondary air 36 into the combustion chamber 2.
  • the fail-safe position of the flap 8 is the flap-closed position. This is through the between outside Plenum 32 and annular combustion chamber interior available pressure difference ensured.
  • the flap 8 can be additionally pressed by springs 16, such as torsion springs on the abutment side, to the encircling collar 14 in the support structure 4.
  • FIG. 19 shows an embodiment of an actuator 24 for a flap 8 with turbine-side stop 15.
  • This actuator 24 is the in the FIG. 13 shown similar.
  • the fail-safe position is reached here but with the cylinder extended, which is ensured by a spring bias 49.
  • a stop 50 may be provided for a defined end position.
  • the flap 8 opens by retraction of the piston 42.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP13160969.5A 2013-03-26 2013-03-26 Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire Withdrawn EP2784393A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13160969.5A EP2784393A1 (fr) 2013-03-26 2013-03-26 Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire
PCT/EP2014/053382 WO2014154401A1 (fr) 2013-03-26 2014-02-21 Chambre de combustion de turbine à gaz avec volets d'aération secondaires

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13160969.5A EP2784393A1 (fr) 2013-03-26 2013-03-26 Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire

Publications (1)

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EP2784393A1 true EP2784393A1 (fr) 2014-10-01

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EP13160969.5A Withdrawn EP2784393A1 (fr) 2013-03-26 2013-03-26 Chambre de combustion d'une turbine à gaz avec des clapets d'air secondaire

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EP (1) EP2784393A1 (fr)
WO (1) WO2014154401A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015176902A1 (fr) * 2014-05-20 2015-11-26 Siemens Aktiengesellschaft Système de turbine
WO2016124348A1 (fr) 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Chambre de combustion annulaire comprenant un segment de dérivation
CN106524222A (zh) * 2015-09-10 2017-03-22 三菱日立电力系统株式会社 燃气轮机燃烧器
EP3660293A1 (fr) * 2018-11-29 2020-06-03 Siemens Aktiengesellschaft Procédé de surveillance de la fonction de soupapes de dérivation dans une turbine à gaz et installation de turbine à gaz

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015207803A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Gasturbinenanlage

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2684572A (en) * 1949-12-12 1954-07-27 Babcock & Wilcox Co Segmental wall construction for combustion apparatus
US3731484A (en) * 1967-11-10 1973-05-08 Lucas Ltd Joseph Apparatus for regulation of airflow to flame tubes for gas turbine engines
JPS5855622A (ja) * 1981-09-30 1983-04-02 Hitachi Ltd 低ＮＯｘガスタ−ビン燃焼器
EP1363077A2 (fr) * 2002-05-14 2003-11-19 Mitsubishi Heavy Industries, Ltd. Chambre de combustion pour turbine à gaz et méthode associée de contrôle de combustion

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2684572A (en) * 1949-12-12 1954-07-27 Babcock & Wilcox Co Segmental wall construction for combustion apparatus
US3731484A (en) * 1967-11-10 1973-05-08 Lucas Ltd Joseph Apparatus for regulation of airflow to flame tubes for gas turbine engines
JPS5855622A (ja) * 1981-09-30 1983-04-02 Hitachi Ltd 低ＮＯｘガスタ−ビン燃焼器
EP1363077A2 (fr) * 2002-05-14 2003-11-19 Mitsubishi Heavy Industries, Ltd. Chambre de combustion pour turbine à gaz et méthode associée de contrôle de combustion

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015176902A1 (fr) * 2014-05-20 2015-11-26 Siemens Aktiengesellschaft Système de turbine
WO2016124348A1 (fr) 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Chambre de combustion annulaire comprenant un segment de dérivation
DE102015202097A1 (de) 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ringbrennkammer mit Bypasssegment
CN106524222A (zh) * 2015-09-10 2017-03-22 三菱日立电力系统株式会社 燃气轮机燃烧器
CN106524222B (zh) * 2015-09-10 2020-04-03 三菱日立电力系统株式会社 燃气轮机燃烧器
EP3660293A1 (fr) * 2018-11-29 2020-06-03 Siemens Aktiengesellschaft Procédé de surveillance de la fonction de soupapes de dérivation dans une turbine à gaz et installation de turbine à gaz

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Publication number Publication date
WO2014154401A1 (fr) 2014-10-02

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