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WO2016066539A1 - Turbine à gaz avec dispositif de freinage par impulsions - Google Patents

Turbine à gaz avec dispositif de freinage par impulsions Download PDF

Info

Publication number
WO2016066539A1
WO2016066539A1 PCT/EP2015/074584 EP2015074584W WO2016066539A1 WO 2016066539 A1 WO2016066539 A1 WO 2016066539A1 EP 2015074584 W EP2015074584 W EP 2015074584W WO 2016066539 A1 WO2016066539 A1 WO 2016066539A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
pulse
braking device
compressor air
compressor
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.)
Ceased
Application number
PCT/EP2015/074584
Other languages
German (de)
English (en)
Inventor
Marco Link
Nicolas Savilius
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
Publication of WO2016066539A1 publication Critical patent/WO2016066539A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/006—Arrangements of brakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/90—Braking
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/06—Purpose of the control system to match engine to driven device
    • F05D2270/061—Purpose of the control system to match engine to driven device in particular the electrical frequency of driven generator

Definitions

  • the present invention relates to a gas turbine with a pulse braking device and to a method for operating such a gas turbine.
  • the mastery of load shedding during operation of a gas turbine provides the operator a major chal ⁇ tion.
  • Load shedding can be made through different load preparation ⁇ che from different first operating conditions in different second operating states. Thus, for example. Be done to idle a load ⁇ mound from the base load out.
  • a load shedding from a partial load operation into an island operation can take place. In this isolated operation must be le ⁇ diglich sufficient electrical energy available ge ⁇ is to operate the gas turbine power plant comprehensive ⁇ device.
  • the emergency shutdown requires the restart of a gas turbine, which is not only time consuming but economically extremely undesirable. In this respect, it is always the endeavor of the operator bers the gas turbine, an emergency shutdown, ie to avoid a trip.
  • Compressor entry grid to reduce as quickly as possible. Since both operational changes must be made over a very short time interval, it often turns out that a safe and above all controlled operation during the load shedding difficult or insufficient can be achieved.
  • Load shedding can be made sufficiently fast, but the target operating state is controlled controlled.
  • This object of the invention underlying problem can be solved by a gas turbine according to claim 1 and a method for operating such a gas turbine according to claim 7.
  • the object on which the invention is based can be achieved by a gas turbine having at least one removal line for removing compressor air, in particular compressor discharge air, which is fluidically connected to an impulse braking device, so that the
  • Compressor air in the pulse braking device forms a directed flow on blade elements, wherein the flow ⁇ direction exerts an impulse on the blade elements, the direction of the intended direction of movement of the rocker elements is directed opposite.
  • the load shedding differs significantly from a normal change in performance of a gas turbine, which, for example, can be carried out in partial load operation.
  • a power change namely, the network synchronization is always present, so that the network acts on the torque of the gas turbine, for example, to avoid over-speed operation.
  • Initiation of a load reduction is typically carried out by appropriate control engineering or control engineering ⁇ Sig nal. Execution of the invention it is generally possible to know the introduction of load shedding ⁇ than that time to it, to which about the network synchronization is abandoned.
  • compressor air is generally used in the sense of
  • the term of the vane elements in the present case is to be understood generally as a device which has a suitable shape, so that an impulse against the direction of movement of the relevant vane element can be exerted on it with appropriate flow through the directional flow.
  • the BEWE ⁇ supply direction of the blade members should in this case relate to the operation according to the direction of movement, including the direction of movement, having the blade elements at noncompliant operation of the gas turbine.
  • the rotor is stunted.
  • the work is applied by the compressor air or compressor discharge air, which is translated in the pulse braking device into a corresponding braking force.
  • the braking force is transmitted to the rotor by means of the blade elements of the pulse braking device, whereby the rotational speed can be reduced when the gas turbine is used as intended.
  • the pulse braking device transmits a pulse against the rotor rotation direction to the rotor, so that a deceleration of the rotor can take place.
  • Such deceleration can be applied to both single-shaft and multi-shaft gas turbines, but the pulse braking device with the rotor unit to be braked must be correspondingly rotationally connected.
  • Compressor air is supplied to the combustion chamber, resulting in a larger fuel-air ratio in the combustion chamber which also causes the burner flame can burn more stable. Moreover, it is relaxed by decreasing the fuel-air ratio less mass flow in the Ent ⁇ voltage turbine of the gas turbine, and consequently reacted Weni ⁇ ger thermal energy into rotary mechanical energy. The reduction of the Ansaugmassenstroms thus also promotes a simultaneous reduction in the power conversion by the gas turbine.
  • the present invention thus permits not only a faster load shedding, but also an improved control of the target operational state after the Lastab ⁇ litter.
  • Compressor air suitably adjust by means of an adjusting, so possibly also during the load shedding the amount of removed compressor air or
  • Compressor air to vary advantageously. Such a setting thus also promotes the stability of the target operating state again.
  • the pulse braking device is designed as expansion turbine of the gas turbine and the blade ⁇ elements are the blades of the expansion turbine.
  • An expansion turbine in this case relates to a device which is vorgese ⁇ hen in the context of regular operation of the gas turbine to relax hot gas from the combustion chamber while converting thermal energy into rotational mechanical energy.
  • the pulse brake device is therefore identical to an expansion turbine, wherein the at least one extraction line is fluidly coupled to the expansion turbine.
  • the extraction line has a feed section in the expansion turbine, which allows the directed flow to be formed on the rotor blades of the expansion turbine.
  • the rotor blades have an aerodynamically adapted geometry, so that with appropriate application of the directed flow on the blades, an impulse can be transmitted to the same, which is directed against the intended direction of rotation of the blades.
  • the expansion turbine thus enables a faster and more controlled execution of the load shedding in the sense of a pulse braking device.
  • Brake turbine is formed, which is not identical to a ⁇ for drinks cycle turbine of the gas turbine, but insbesonde ⁇ re is coupled to such a rotating mechanically and Blade elements are blades of the brake turbine.
  • a braking turbine is used herein only the generation of a braking torque, without, however, the hot gas would be released via the brake ⁇ turbine to convert thermal energy in approximately rotating mechanical energy.
  • it is.
  • Possible to provide a brake turbine which must meet technically much lower Anforderun ⁇ gen than about an expansion turbine of a gas turbine, to be coupled to such an expansion turbine navmecha ⁇ cally, so that the braking torque from the brake turbine to the rotor of the expansion turbine is transmitted.
  • the brake turbine may also be provided on other rotors in multi-shaft gas turbines.
  • the brake turbine can thus be used relatively inexpensively wherever this is required accordingly.
  • it can be dispensed with as a Ent ⁇ voltage turbine of a gas turbine fluidly to such ⁇ fit that they can be used as a pulse brake device.
  • the pulse braking device has at least one nozzle element, via which the
  • Compressor air is supplied from the extraction line of the pulse braking device to form the directional flow.
  • the at least one nozzle element not only allows a locally targeted flow guidance, but also allows the flow rate to be increased, whereby a relatively high impulse can be provided by the directional flow in the impulse braking device.
  • WEI terhin at least allows a nozzle member from the ⁇ forming a directed flow without any further flow-guiding elements in free space over a relatively large distance away.
  • the pulse emitted by the directed flow can also be used away at a relatively greater distance from the nozzle element. This is particularly advantageous in the construction of the pulse braking device, since thus lower requirements can be placed on their geometry.
  • the pulse braking device comprises a plurality of nozzle elements, which are distributed over a circumference in the pulse braking device, and which are adapted to form respective directed flows and to impinge the blade elements with pulses, wel ⁇ che the intended Direction of movement of the blade elements are directed opposite.
  • the plurality of nozzle elements it is possible, in particular distributed over the circumference of the pulse braking device, to uniformly load the blade elements with a respectively directed flow.
  • all blade elements are on the one hand ver ⁇ proportionate applied evenly with a pulse, and on the other hand the size of the can, with the same total momentum
  • the pulse braking device has at least one bore in a guide vane carrier, via which the compressor air from the extraction line of the pulse ⁇ braking device is supplied to form the directed flow.
  • the pulse braking device has at least one guide blade, which is fastened to the pulse braking device by means of a guide blade carrier.
  • the guide vane carrier is relatively stable and usually made of solid material, so that the directional flow can be formed si- and controlled.
  • the at least one bore may be provided in a technically adapted guide vane.
  • Removal quantity may result from the technical limitations or conditions of the compressor or from the technical limitations of the compressor extraction and the local load capacity of the individual blade elements.
  • the minimum discharge quantity of at least 3% of the compressor mass flow which is carried out in accordance with the invention , permits sufficient braking power to be made available during normal operation, so that an effective contribution to speed reduction during load shedding of a gas turbine can be achieved.
  • Compressor air or compressor end air which is passed to the show ⁇ fel elements in the pulse braking device, an average flow velocity of at least 250 m / s on ⁇ has. Again, a maximum flow rate in turn results from the technical limitations or conditions. At a minimum average flow rate of 250 m / s and an assumed average amount of withdrawn via the withdrawal line
  • Compressor air or Ver Whyrend Kunststoff a sufficiently large pulse can be provided, which can come to an effectively effective contribution to the speed reduction.
  • Figure 1 is a schematic representation of a first embodiment of the gas turbine according to the invention from the side;
  • Figure 2 is a schematic representation of another embodiment of the gas turbine according to the invention from the side;
  • FIG. 3 shows an embodiment of the method according to the invention in a flowchartatic representation.
  • FIG. 1 shows a first embodiment of a erfindungsge ⁇ MAESSEN gas turbine 10, which in addition to a compressor 11, a combustion chamber 12 and an expansion turbine 13, which is rotatably coupled via the rotor 14 to the compressor 11 comprises.
  • a generator 15 is provided to provide electrical energy, which is obtained from the rotational energy of the rotor 14.
  • an extraction line 20 is arranged, but which can also apparent ⁇ compressor air compressor end present general my (this is the withdrawal line 20 is not of course in the field of
  • an actuator 21 (such as a flow valve) is provided, by means of which the amount of on the
  • Extraction line 20 removed compressor discharge air can be adjusted.
  • the compressor discharge air is in the region of Ent ⁇ tension turbine 13 via at least one nozzle member 36 der- introduced into the expansion turbine that the resulting directed nozzle flow, or the plurality of directed currents, on the rotating blade elements
  • Operation of the gas turbine is directed against.
  • the expansion turbine 13 is presently designed as a pulse ⁇ brake device 30, in which a directed flow from the nozzle member 36 so on the Schaufelele ⁇ elements 35 hits that a pulse is transmitted to the blade elements whose direction of the intended direction of movement of the blade elements 35 directed counter is.
  • the blade elements 35 are designed as rotor blades, with the blade elements 35 being firmly connected to the rotor 14 so far that the pulse can be transmitted to them as a whole.
  • the amount of compressor air which is the combustion chamber 12 supplied ⁇ leads to decrease can by means of the actuator 21, the amount of compressor air which may be removed via the extraction line 20 may be adjusted accordingly.
  • the blade elements 35 of the expansion turbine 13 are subjected to a braking force, so that an overspeed operation can be counteracted.
  • the nozzle member 36 is replaced by a circumferentially in cross section with respect to the expansion turbine 13 ⁇ arranged plurality of nozzle elements.
  • FIG. 2 shows a further embodiment of the gas turbine 10 according to the invention in a schematic representation from the side, wherein, unlike in the embodiment shown in FIG. 1, the gas guided through the withdrawal conduit 20 is now shown in FIG.
  • Compressor air not the expansion turbine 13 but a supplied as a brake turbine pulse brake device 30 is supplied.
  • the Impulsbremsvor ⁇ device 30 designed as a brake turbine can be comparable crudebil ⁇ det essentially in terms of their braking function of a relaxation turbine 13, but the size and the materials as well as the geometry must meet significantly lower requirements.
  • the brake turbine is in this case rotatably mechanically coupled to the Ro ⁇ gate 14 so that a braking torque on the rotor 14 and all the components connected to it is transmitted upon activation of the designed as a braking device Bremsturbi ⁇ ne 30th
  • FIG. 3 shows, in a flow diagram, an embodiment of the method according to the invention for operating a gas turbine shown above, which comprises the following steps:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne une turbine à gaz (10) comprenant au moins une conduite de prélèvement (20) destinée à prélever de l'air de compresseur, notamment de l'air final de compresseur, laquelle est raccordée en technique des fluides à un dispositif de freinage par impulsions (30), de sorte que l'air de compresseur forme dans le dispositif de freinage par impulsions (30) un écoulement dirigé sur les éléments en aube (35). Le sens de l'écoulement provoque une impulsion sur les éléments en aube (35), dont la direction est orientée à l'opposé du sens de déplacement des éléments en aube (35) conformément à leur usage.
PCT/EP2015/074584 2014-10-30 2015-10-23 Turbine à gaz avec dispositif de freinage par impulsions Ceased WO2016066539A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014222191.9 2014-10-30
DE102014222191 2014-10-30

Publications (1)

Publication Number Publication Date
WO2016066539A1 true WO2016066539A1 (fr) 2016-05-06

Family

ID=54366192

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2015/074584 Ceased WO2016066539A1 (fr) 2014-10-30 2015-10-23 Turbine à gaz avec dispositif de freinage par impulsions

Country Status (1)

Country Link
WO (1) WO2016066539A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111902608A (zh) * 2018-03-29 2020-11-06 三菱动力株式会社 单轴联合循环设备、单轴联合循环设备的测试方法及单轴联合循环设备的控制装置
FR3114608A1 (fr) * 2020-09-29 2022-04-01 Safran Aircraft Engines Procédé de commande d’une turbomachine visant à éviter les survitesses

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3008688A (en) * 1957-06-05 1961-11-14 Fairchild Stratos Corp Overspeed safety check for turbines
US20100028126A1 (en) * 2007-07-17 2010-02-04 General Electric Company Apparatus and method for controlling a rotary machine using pressurized gas

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3008688A (en) * 1957-06-05 1961-11-14 Fairchild Stratos Corp Overspeed safety check for turbines
US20100028126A1 (en) * 2007-07-17 2010-02-04 General Electric Company Apparatus and method for controlling a rotary machine using pressurized gas

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111902608A (zh) * 2018-03-29 2020-11-06 三菱动力株式会社 单轴联合循环设备、单轴联合循环设备的测试方法及单轴联合循环设备的控制装置
CN111902608B (zh) * 2018-03-29 2022-08-19 三菱重工业株式会社 单轴联合循环设备、单轴联合循环设备的测试方法及单轴联合循环设备的控制装置
US11572841B2 (en) 2018-03-29 2023-02-07 Mitsubishi Heavy Industries, Ltd. Single-shaft combined cycle plant, testing method for single-shaft combined cycle plant, and control device for single-shaft combined cycle plant
FR3114608A1 (fr) * 2020-09-29 2022-04-01 Safran Aircraft Engines Procédé de commande d’une turbomachine visant à éviter les survitesses

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