EP1380723A1 - Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif - Google Patents

Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif Download PDF

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Publication number
EP1380723A1
EP1380723A1 EP02015281A EP02015281A EP1380723A1 EP 1380723 A1 EP1380723 A1 EP 1380723A1 EP 02015281 A EP02015281 A EP 02015281A EP 02015281 A EP02015281 A EP 02015281A EP 1380723 A1 EP1380723 A1 EP 1380723A1
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EP
European Patent Office
Prior art keywords
cooling fluid
turbine
preswirler
blades
accelerated
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Withdrawn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
EP02015281A
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German (de)
English (en)
Inventor
Peter Tiemann
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 EP02015281A priority Critical patent/EP1380723A1/fr
Publication of EP1380723A1 publication Critical patent/EP1380723A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc

Definitions

  • the invention relates to a method for cooling on one rotatable rotor of a turbine fixed blades by means of a cooling fluid.
  • the invention further relates to a turbine that can be cooled according to the invention and a preswirler for use in a turbine which can be cooled in accordance with the invention.
  • turbines are used to generate energy from a fluid flowing through the turbine into a mechanical one To convert energy, in particular into a rotational energy.
  • axial turbines are used to get out to gain mechanical energy from a hot gas.
  • gas turbines are referred to as gas turbines.
  • the turbine has an arrangement of energy in its flow channel from rotor blades and guide vanes. Because of the direct Influence of the gas on the guide and rotor blades are this, especially at high gas temperatures, cooled.
  • To the guide and rotor blades each have a channel system on which a cooling fluid can flow through. In the state In technology, the coolant is known to the guide vanes Fed way.
  • the cooling fluid for rotating on one rotor blades mounted on a rotor axial end fed to the rotor and a arranged in the rotor Channel system directed to the appropriate blades.
  • the invention provides a method for cooling of a rotatably mounted rotor shaft Turbine attached blades by means of one in the blades provided cooling channels flowing cooling fluid proposed, which from a cooling fluid source by means of the guide vanes of the turbine to the head side guided on the guide blades provided Preswirlers and by means of the preswirler in a related to the blades radial and based on the flow direction of the turbine accelerated in the same direction and in the exit openings the preswirler arranged opposite openings the rotor shaft and further into the cooling channels of the rotor blades flows in, the cooling fluid by means of the preswirler also is accelerated against the direction of flow of the turbine.
  • the method according to the invention can be used for the first time be that the blades over the guide blades as needed be supplied with cooling fluid, namely both upstream of the guide vanes in the direction of flow of the turbine as well as downstream blades can be supplied with cooling fluid. Conveniently this leads to the Cooling fluids have a positive flow behavior.
  • An advancement of cooling fluid through an axial end of the rotor shaft can be avoided.
  • it can be the supply with cooling fluid according to an arrangement of the blades in Direction of flow of the turbine may be predetermined, or it can set the cooling according to a performance state become.
  • a cooling fluid supply can Impeller at the gas inlet of the turbine opposite one Blade arrangement at the gas outlet of the turbine forced his.
  • a cooling fluid supply can also be adapted so that that high efficiency is achieved.
  • both shaft ends for connection other rotating machines and / or gears are available stand.
  • the cooling of the blades can also be set that the blades regardless of their position based on the flow direction within the barrel and Guide vane arrangement are thermally evenly loaded.
  • Cooling fluid flows namely flows cooling fluid accelerated against the direction of flow in openings of the cooling channels from upstream Blades while accelerating in the direction of flow Cooling fluid flows into the openings of the downstream barrel.
  • a separation of the cooling fluid flows can be advantageous can be achieved.
  • the in the flow direction of the turbine and that against the flow direction the turbine also accelerated the cooling fluid tangentially to the direction of rotation of the rotor and in its direction of rotation is accelerated.
  • the cooling fluid flow thus has the Leave the fixed coolant guide elements tangential speed component related to the direction of rotation of the rotor on making the transition to those on the Rotor shaft arranged rotating coolant openings advantageous facilitated.
  • the cooling fluid through the preswirler tangential to the direction of rotation of the rotor and accelerates its direction of rotation. This is advantageously done the tangential acceleration of the cooling fluid in the transition of the fixed coolant guide elements, the Preswirlers arranged on the head side of the guide vanes the rotating components of the turbine.
  • the cooling fluid from the Preswirlers alternate with upstream ones Blades and downstream in the direction of flow Blades are flowing. Mutual influences of the cooling fluid flows can be reduced.
  • the cooling fluid can Example using a special channel arrangement in the direction the corresponding openings of the cooling channels of the blades be performed. Different needs-based cooling of blades arranged progressively in the direction of flow can be reached. So the cooling fluid can everyone Blade area regardless of relative position are fed in the direction of flow to the guide vanes.
  • the acceleration can be, for example, by a suitable one Design of the channels can be achieved.
  • cooling fluid from the Preswirlers both forward and in the direction of flow downstream blades flows.
  • One can be advantageous great homogeneity in the supply with the moving blades can be achieved with cooling fluid.
  • the flow of the Cooling fluids are divided, the partial flows each flow upstream or downstream of the blades.
  • cooling fluid in the rotor shaft is accelerated in the radial direction. So it can Cooling fluid advantageously supplied to each area of the blades be even marginal areas that only have long capillary channels can be supplied with cooling fluid.
  • the acceleration can e.g. achieved by a suitable channel become.
  • Air can be provided inexpensively known means for establishing a cooling air supply can be used.
  • others can Substances, especially inert gases like helium, but also Gases such as carbon dioxide, nitrogen, or gas mixtures thereof and the like can be used.
  • inert gases like helium
  • Gases such as carbon dioxide, nitrogen, or gas mixtures thereof and the like can be used.
  • the cooling fluid with the process gas is not reacts, or that the coolant forms a protective film, which in addition to thermal protection for the bucket also one Protects against corrosion.
  • a turbine in particular gas turbine, with arranged on a rotatably mounted rotor shaft Blades and connected to a housing of the turbine Guide vanes suggested by a cooling fluid
  • a cooling fluid in particular gas turbine, with arranged on a rotatably mounted rotor shaft Blades and connected to a housing of the turbine Guide vanes suggested by a cooling fluid
  • Preswirlers are arranged at the head, by means of which the Cooling fluid in a radial and relative to the barrel blades based on the direction of flow of the turbine same direction can be accelerated and has the outlet openings, opposite the blades associated with cooling channels of the barrel Entry openings are arranged, the preswirler have a channel arrangement by means of which the cooling fluid can also be accelerated against the direction of flow of the turbine is.
  • a cooling fluid supply accordingly a thermal load can be predetermined, the in the flow direction offset bucket wheels independently of each other can be supplied with cooling fluid. Modelability is advantageous the cooling fluid flow achievable.
  • the rotor shaft is a channel system for accelerating the cooling fluid has in the radial direction of the rotor shaft. So can good cooling even in the marginal areas of individual blades can be achieved. A reduction in the cross-section of the duct can also occur can be achieved. This is especially true for the Cooling thin-walled areas of the blades is advantageous, because higher stability can be achieved.
  • the Channel system of the rotor shaft to accelerate the cooling fluid formed in and / or against the flow direction of the turbine is. Aiding the cooling fluid flow for guidance can be reached at any point of the blades to be cooled become.
  • the Cooling fluid simultaneously from one another in the direction of flow arranged guide vanes to arranged in between Blades are directed to a high supply with To reach cooling fluid.
  • a supply from am Turbine blades arranged gas entry through several Guide vanes arranged one behind the other in the flow direction be achieved when an appropriate amount of Cooling fluid is required.
  • sealing element is arranged between the preswirler and the rotor shaft. It is advantageous the sealing element is arranged such that at the cooling fluid outlet before and after the preswirler in the flow direction Temperature and pressure conditions can be achieved. Compensatory flows can be largely avoided.
  • the sealing element can be, for example, a labyrinth seal or by an elastic, grinding Seal be formed.
  • the sealing element is attached to the preswirler. Loads on the sealing element due to rotation can be avoided. Furthermore, an influence on the rotational properties of the rotor shaft can such as moment of inertia, imbalance and the like avoided become.
  • the sealing element on the Rotor shaft can be arranged, for example, a simple Design and attachment option of the sealing element to accomplish. So the sealing element can be extensive be arranged on the rotor shaft surface.
  • a preswirler is also used in a turbine for placement on one of a cooling fluid flow-through guide vane with a channel arrangement proposed, the input side with an outlet opening of the Guide vane for the cooling fluid can be connected, and on the output side opens into an outlet opening opposite Inlet openings of the cooling channels of the blades are arranged are, through the channel arrangement, the cooling fluid in a radial with respect to the blades and relative to the Flow direction of the turbine can be accelerated in the same direction is, the channel arrangement for accelerating the cooling fluid also for acceleration against the direction of flow the turbine is provided.
  • the preswirler can easy way to carry out the invention Create procedure, especially if preswirler already part the turbine are. In this case, the invention Function by providing an appropriate channel arrangement can be realized without additional components are needed.
  • neighboring preswirler inlet openings alternate are connected to channels of the channel arrangement, by means of which the cooling fluid in and against the flow direction of the Turbine is accelerable.
  • the guide vanes are advantageous supplied cooling fluid alternately in the direction of flow Upstream or downstream blades supplied. A further reduction in mutual interference is reachable.
  • the channel arrangement of the preswirler bifurcations has, by means of which the cooling fluid in and against the Flow direction of the turbine can be accelerated. So can for example, the effort for the channel arrangement is reduced be, namely when in the direction of flow of the cooling fluid a common acceleration channel is provided for the fork is the acceleration radially with respect to the blade causes. The section following the fork the channel arrangement causes the corresponding accelerations in or against the flow direction the turbine.
  • the Channel arrangement of the preswirler is designed such that the Cooling fluid additionally tangential to the direction of rotation of the rotor and can be accelerated in the direction of rotation.
  • the cooling fluid flow indicates when leaving the fixed Preswirler a tangential related to the direction of rotation of the rotor Speed component on the transition to the rotating coolant openings arranged on the rotor shaft advantageously relieved.
  • the direction of the tangential Speed component of the cooling fluid corresponds to that of the Rotary movement of the rotor.
  • the head end the Preswirler has a receptacle for a sealing element.
  • the sealing element with the preswirler can be advantageous get connected. Furthermore, an influence on the mechanical Properties of the rotor shaft largely avoided become.
  • the receptacle can be through a recess like a groove be formed in the one fastening end of the sealing element is arranged fixable.
  • Fig. 1 shows a circuit diagram of a schematic flow of inventive method.
  • air used as cooling fluid from a container 10 over a duct arrangement 40 is fed to the turbine.
  • the turbine According to the method are mounted on a rotatably mounted rotor shaft 30 the blades attached to the turbine 26, 28 by means of the in blades 26, 28 provided cooling channels 44 flowing through the barrel Cooled air cooled by the cooling air source 10 by means of channels provided in the turbine guide vanes 42 14 provided on the head side on the guide vanes 42 Preswirlind 20 is headed.
  • the preswirler 20 By means of the preswirler 20 the cooling air into a radial with respect to the blades 26, 28 and related to the direction of flow 46 of the turbine the same direction accelerates and flows into the outlet openings 48 of the preswirler 20 arranged opposite one another Blade openings 26 of the cooling channels of the barrel 26, 28 into it.
  • the cooling air is inventively by means of the preswirler 20 also accelerated against the flow direction 48 of the turbine.
  • Cooling air are separate outlet openings 48 of the Preswirler 20 and opposite entry openings 50 of the rotor shaft 30 is provided.
  • the cooling air flows from the preswirlers 20 at the same time to upstream and downstream in flow direction 46 Blades 26, 28.
  • the preswirler 20 have fork 24 on which the cooling air on the channels 34, 36th the preswirler 20 distributed.
  • the channels 34, 36 each open at openings 48, the openings 50 opposite the rotor shaft side are arranged.
  • the cooling air is related to the Blades 26, 28 accelerated in the radial direction.
  • the cooling air flows into a channel system 44 of the moving blades 26, 28 into it.
  • the cooling air flows through the blades 26, 28 provided channels 44, which are not shown Outlet openings of the runner blades 26, 28 open, where the cooling air flows out.
  • Fig. 4 shows a section of a Preswirler 20 in the forked Version.
  • the openings 18 are provided on the input side, via which the cooling air is supplied from the guide vanes 42 becomes.
  • Each opening 18 is provided with a channel each connected to a fork 24. From the fork 24 two channels 34, 36 each extend from the outlet openings 48 of the preswirlers 20 open.
  • a preswirler 20 Fig. 3 shows a section in which the cooling air alternately to guide vanes arranged upstream in the flow direction 46 26 and downstream in the flow direction 46 blades 28 streams.
  • the inlet openings 18 are the preswirlers 20 alternately via channels 52 with outlet openings 48 connected, the channels 52 alternately accelerating the cooling air in or against the flow direction 46 of the turbine.
  • Fig. 2 shows a section of a longitudinal section of an inventive Turbine.
  • the channel arrangement 40 connected to the channels 14 the guide vanes 42 are connected.
  • the channels 14 of the guide vanes 42 open out at the top of openings 16.
  • the openings 18 are arranged on the guide vanes 42
  • Preswirler 20 provided the duct systems according to Fig. 3 have.
  • the preswirlers 20 effect a corresponding acceleration of the cooling air, so that these through the outlet openings 48 and those with the Inlet openings 50 connected channels 44 of the blades 26, 28 flows.
  • Cooling air supply can be achieved.
  • Fig. 5 shows a section of a longitudinal section through a gas turbine with cooling fluid supply as in Fig. 2, wherein in contrast to the embodiment in Fig. 2 here on the head Sealing element provided at the end of the preswirler 54 is arranged.
  • the sealing element 54 effects on the rotor shaft side a fluidic separation of the upstream Blades 26 flowing cooling fluid from to Subordinate barrel blades 28 flowing cooling fluid.
  • this Design points to the upstream blades 26 flowing cooling fluid a lower temperature than that to the downstream blades 28 flowing cooling fluid on.
  • FIG. 2 shows a section of a longitudinal section through a gas turbine with cooling fluid supply as in Fig. 2, wherein in contrast to the embodiment in Fig. 2 here on the head Sealing element provided at the end of the preswirler 54 is arranged.
  • the sealing element 54 effects on the rotor shaft side a fluidic

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02015281A 2002-07-09 2002-07-09 Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif Withdrawn EP1380723A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02015281A EP1380723A1 (fr) 2002-07-09 2002-07-09 Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02015281A EP1380723A1 (fr) 2002-07-09 2002-07-09 Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif

Publications (1)

Publication Number Publication Date
EP1380723A1 true EP1380723A1 (fr) 2004-01-14

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EP02015281A Withdrawn EP1380723A1 (fr) 2002-07-09 2002-07-09 Procédé de refroidissement d'aubes de turbine, dispositif induisant une prérotation de fluide, ainsi que turbine comprenant ledit dispositif

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EP (1) EP1380723A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1676977A1 (fr) * 2004-12-29 2006-07-05 Siemens Aktiengesellschaft Turbine à gaz comprenant une tuyère de tourbillonnement et procédé de fonctionnement d'une telle turbine
EP1911948A2 (fr) * 2006-10-04 2008-04-16 Basf Se Production d'énergie dans une turbine à gaz dotée d'une alimentation en gaz contenant du dioxyde de carbone
EP2358978B1 (fr) 2008-11-17 2017-06-28 Rolls-Royce Corporation Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
US20180298774A1 (en) * 2017-04-18 2018-10-18 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
US20180298770A1 (en) * 2017-04-18 2018-10-18 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
FR3115562A1 (fr) * 2020-10-26 2022-04-29 Safran Aircraft Engines Injecteur d’air de refroidissement pour turbine de turbomachine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2896906A (en) * 1956-03-26 1959-07-28 William J Durkin Turbine cooling air metering system
US3015937A (en) * 1958-07-03 1962-01-09 James V Giliberty Temperature modulating system for internal combustion turbines and the like
GB938247A (en) * 1962-03-26 1963-10-02 Rolls Royce Gas turbine engine having cooled turbine blading
US3535873A (en) * 1967-10-24 1970-10-27 Joseph Szydlowski Gas turbine cooling devices
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
DE19824766A1 (de) * 1998-06-03 1999-12-09 Siemens Ag Gasturbine sowie Verfahren zur Kühlung einer Turbinenstufe

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2896906A (en) * 1956-03-26 1959-07-28 William J Durkin Turbine cooling air metering system
US3015937A (en) * 1958-07-03 1962-01-09 James V Giliberty Temperature modulating system for internal combustion turbines and the like
GB938247A (en) * 1962-03-26 1963-10-02 Rolls Royce Gas turbine engine having cooled turbine blading
US3535873A (en) * 1967-10-24 1970-10-27 Joseph Szydlowski Gas turbine cooling devices
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited Gas turbine engine cooling system
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
DE19824766A1 (de) * 1998-06-03 1999-12-09 Siemens Ag Gasturbine sowie Verfahren zur Kühlung einer Turbinenstufe

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1676977A1 (fr) * 2004-12-29 2006-07-05 Siemens Aktiengesellschaft Turbine à gaz comprenant une tuyère de tourbillonnement et procédé de fonctionnement d'une telle turbine
WO2006072528A1 (fr) * 2004-12-29 2006-07-13 Siemens Aktiengesellschaft Turbine a gaz comportant un generateur de prerotation et procede d'utilisation d'une turbine a gaz
EP1911948A2 (fr) * 2006-10-04 2008-04-16 Basf Se Production d'énergie dans une turbine à gaz dotée d'une alimentation en gaz contenant du dioxyde de carbone
EP1911948A3 (fr) * 2006-10-04 2014-02-19 Basf Se Production d'énergie dans une turbine à gaz dotée d'une alimentation en gaz contenant du dioxyde de carbone
EP2358978B1 (fr) 2008-11-17 2017-06-28 Rolls-Royce Corporation Appareil et procédé de refroidissement d un agencement de partie profilée de turbine dans une turbine à gaz
US20180298774A1 (en) * 2017-04-18 2018-10-18 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
US20180298770A1 (en) * 2017-04-18 2018-10-18 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
EP3392458A1 (fr) * 2017-04-18 2018-10-24 United Technologies Corporation Turbine avec injecteur de bord tangentiel tourné vers l'amont
EP3392457A1 (fr) * 2017-04-18 2018-10-24 United Technologies Corporation Turbine avec injecteur de bord tangentiel tourné vers l'amont
US10458266B2 (en) * 2017-04-18 2019-10-29 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
FR3115562A1 (fr) * 2020-10-26 2022-04-29 Safran Aircraft Engines Injecteur d’air de refroidissement pour turbine de turbomachine

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