EP3199760A1 - Aube de turbine dotée d'un élément d'étranglement - Google Patents

Aube de turbine dotée d'un élément d'étranglement Download PDF

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Publication number
EP3199760A1
EP3199760A1 EP16153376.5A EP16153376A EP3199760A1 EP 3199760 A1 EP3199760 A1 EP 3199760A1 EP 16153376 A EP16153376 A EP 16153376A EP 3199760 A1 EP3199760 A1 EP 3199760A1
Authority
EP
European Patent Office
Prior art keywords
opening
turbine blade
side wall
throttle element
airfoil
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Withdrawn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
EP16153376.5A
Other languages
German (de)
English (en)
Inventor
York Mick
Andreas Heselhaus
Robert Kunte
Uwe Paul
Bärbel Pöhler
Marcel SCHLÖSSER
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 EP16153376.5A priority Critical patent/EP3199760A1/fr
Publication of EP3199760A1 publication Critical patent/EP3199760A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/191—Two-dimensional machined; miscellaneous perforated

Definitions

  • the invention relates to a turbine blade for a thermal turbomachine, comprising an airfoil which can be flowed around by a hot gas and which has a suction-side sidewall and a pressure-side sidewall, which in the main flow direction of the hot gas is viewed from a common leading edge to a trailing edge and along a direction to the main flow direction Substantially perpendicular longitudinal axis extending from a first end of the airfoil to this opposite the second end of the airfoil, wherein in the blade inside at least one cavity is provided, which is bounded by a plurality of inner surfaces, of which at least as a first side wall inner surface at least partially the inside of one of the two Is side walls, and having a feed side through which a cooling medium can be flowed into the cavity from outside the turbine blade, wherein the turbine blade on the feed side, a throttle element comprising at least one opening.
  • a corresponding turbine blade is for example from the WO 2009/153108 A2 known.
  • a throttle plate is provided at the entrance of the cooling air duct, which reduces the amount of cooling medium flowing into the interior of the turbine blade.
  • two throttle holes are provided whose position appears optional.
  • the object of the invention is therefore to provide a turbine blade whose throttle plate enables improved cooling.
  • the at least one opening is arranged as the first opening closer to the first side wall inner surface than to the inner surface which lies opposite the first inner wall side surface.
  • the invention is based on the recognition that, in the case of centrally arranged openings in the throttle element, the cooling air does not uniformly enter into the inlet cross section of the cavity, but rather selectively via local positions with a high momentum. Side of these local positions occur immediately downstream of the throttle element at the channel inlet so-called dead water areas or recirculation areas with low Reynolds numbers, which cause less heat transfer in the cooling channel.
  • the inventive displacement of the openings of the throttle element toward the thermally highly loaded side walls an improved cooling air distribution can be achieved at the partially covered opening cross-section of the cavity.
  • the openings of the throttle element By placing the openings of the throttle element close to the wall, the distance between the side wall inner surface to be cooled and the nearest edge of the relevant opening is reduced, so that the space for dead water or recirculation areas has been significantly reduced. Accordingly, the occurrences of these flow phenomena are lower compared to the throttle elements known in the prior art.
  • This increases the heat transfer there, as a result of which the side walls also become more efficient immediately downstream of the throttle element from the cooling medium passing through can be cooled as before.
  • the targeted cooling of the thermally highly stressed sites can extend the life of the turbine blade and / or possibly delay the formation of defects such as cracks or the like.
  • This invention also allows the selective use of the positive effect of equalizing the flow at the cavity entrance, whereby a strong or a weak cooling in this area of the cooling channel can be adjusted, depending on the design requirement.
  • an opening is then positioned closer to the first sidewall inner surface than to the inner surface opposite it when the centroid of the respective aperture is located closer to said sidewall inner surface than to the inner surface opposite it.
  • the openings provided in the throttle element may have any shape, for example, they may be circular, slit-shaped or elliptical. Slits in particular, which follow the curvature of the side wall or the curvature of the side wall inner surface, are advantageous because they produce a more homogeneous mass flow distribution along the side wall surface in contrast to a plurality of discrete bores. As a result, its allows a complete flow in cavities or cooling channels with highly curved side walls, as they can occur, for example, in guide vanes provide.
  • the turbine blade according to the invention comprises a main body, which has mostly been produced in a casting process, and the one next to the airfoil Also includes a platform and provided for mounting blade root, a inventive, separately manufactured throttle element can also be used as a retrofit solution for existing turbine blades.
  • a center line can be defined centrally on the feed side between the first side wall inner surface and the inner surface opposite it, wherein the at least one opening is arranged eccentrically as the first opening with respect to the center line.
  • this is understood to mean an opening whose opening area is not cut by the center line. This indicates a position of the opening with respect to the side wall inner surface which positions said opening so close to the side wall inner surface that recirculation and dead water areas can be reduced to a technically acceptable size.
  • the inner surface opposite the first side wall inner surface is at least a part of the inner surface of the other of the two side walls as the second side wall inner surface.
  • second openings are preferably provided in the throttle element, wherein the first opening (s) and the second opening (s) are arranged such that the first opening (s) are closer to the first side wall inner surface at the second sidewall inner surface and the second opening (s) are located closer to the second sidewall inner surface than at the first sidewall inner surface.
  • a center line can be defined centrally on the feed side between the first side wall inner surface and the inner surface opposite it, the first opening and the second opening being arranged eccentrically with respect to the center line.
  • the turbine blade can be designed as a guide blade or as a blade of a thermal fluid machine.
  • the throttle element is usually fastened to one of the ends of the blade, whereas with blades the throttle element is fastened to an underside of a blade root of the blade.
  • the cavity extends not only through the blade of the blade, but also through the blade root.
  • the cavity boundary is to be understood by inner surfaces so that they can also extend through a portion of the blade root. Due to the longer inlet distance of the cavity of a blade, however, the use of the throttle element according to the invention is more suitable for guide vanes.
  • the throttle element is plate-shaped. In this case, it only serves to adjust the inflowing coolant quantity.
  • the throttle element may be configured in the form of a cylinder hatch.
  • the term "cylinder-hat-shaped" is understood to mean not a circular but a throttle element which comprises a tubular section with an arbitrary cross-sectional contour, which has a lid at one end and a brim at the other end.
  • baffle cooling openings may be provided in the tubular section, so that parts of one or both side walls are bounce-coolable.
  • the throttle element may have a defined Have thickness that allows an oblique separation of the cooling air openings to the vertical axis of the cooling channel. This is another possibility of optimized cooling downstream of the throttle plate possible.
  • the invention relates to a turbine blade for a thermal turbomachine, comprising a hot air flowable airfoil having a suction side wall and a pressure side sidewall, viewed in a main flow direction of the hot gas, from a common leading edge to a trailing edge and along one in a longitudinal axis substantially perpendicular to the main flow direction, extending from a first end of the airfoil to a second end of the airfoil opposite thereto, wherein in the airfoil interior at least one cavity is provided, which is bounded by a plurality of inner surfaces, of which a first side wall inner surface at least a part of a the two side walls and having a feed side through which a cooling medium can be flowed into the cavity from outside the turbine blade, wherein the turbine blade at the feed side a throttle element with the at least one opening.
  • the at least one opening is arranged as a first opening closer to the first side wall inner surface than on the inner surface, the first side wall inner surface opposite.
  • FIG. 1 shows a partial perspective sectional view of a turbine blade 10, which along a virtual longitudinal axis 12 in succession comprises: an aerodynamically curved airfoil 14, a platform 16 and a fir-tree-shaped blade root 18.
  • the airfoil 14 includes a pressure-side side wall 20 and a suction-side side wall 22, which along a Main flow direction of a hot gas from a common front edge, not shown, to a trailing edge 24 extend.
  • Parallel to the longitudinal axis 12, the airfoil 14 extends from a first, platform-proximal end 26 to an opposite end, which is also not shown.
  • the opposite end is also referred to as the blade tip, on which, if appropriate, a platform referred to as shroud can be arranged.
  • the blade 14 is hollow and has two cavities 28, 30 according to this embodiment. Both cavities 28, 30 serve as cooling channels and are via a deflection, not shown, which is provided on the blade tip, fluidly connected to each other. Due to a rib 32 extending between the pressure-side side wall 20 and the suction-side side wall 22, the two cavities 28, 30 are separated from one another in the airfoil away from the deflection and also in the area of the blade root 18.
  • the cavity 28 has at its entrance to a feed side 34, on which a throttle element 36 is arranged.
  • the throttle element 36 is attached to the remainder of the turbine blade, the cast blade body, in a conventional manner, such as by a welded joint. At the same time, the throttle element 36 has two openings 38, through which the cavity 28 from the outside, a cooling medium K, preferably cooling air, can be fed.
  • the hot gas of the gas turbine flows from the leading edge to the trailing edge 24.
  • the airfoil 14 is internally cooled.
  • the turbine blade 10 is supplied via the openings 38 cooling air, which along the cavity 28, the side walls 20, 22 flows cooling. Arrived at the blade tip, it flows through the deflection, so that it then flows into the cavity 30, with opposite flow direction with respect to the flow direction in the cavity 28. From the cavity 30, the cooling air flows through not further shown cooling air ducts arranged at the trailing edge 24 Outlet openings 40, at which the cooling air leaves the turbine blade 10.
  • the outlet openings 40 are designed as so-called "cut-back openings". However, this is irrelevant to the invention. They could also alternatively be arranged as central outlet openings at the trailing edge 24.
  • the cavity 28 is bounded on the one hand by the inner surfaces 21, 23.
  • the inner surfaces 21, 23 extend from the Blade tip to the throttle element 36.
  • the cavity 28 is also bounded by the inner surface 25 of the rib 32. Another cavity 28 limiting surface is not shown.
  • first and second side wall inner surfaces 31st , 33 denotes, however, these may extend into the blade root.
  • the openings 38 are arranged closer than before to the side wall inner surfaces 31, 33. They are thus outside an imaginary center line 44, which is defined centrally between the two opposite side wall inner surfaces 31, 33.
  • the center line 44 coincides with the position of the longitudinal axis 12.
  • the inner surfaces 21, 23 are opposite each other and are separated by a distance H K , wherein the center line at H K / 2 can be found.
  • the apertures 38 are far enough away from the centerline 44 that their cross-sections are not cut from the centerline 44.
  • a sufficiently large displacement of the opening 38 is achieved from the center of the feed side, to prevent between inner surface 21, 23 and the opening 38, a sufficiently large space is present, in which the unwanted flow phenomena can form.
  • FIG. 2 in perspective partially sectioned view of a trained as a guide blade turbine blade 10th
  • this turbine blade 10 comprises a longitudinal axis 12, an airfoil 14, a platform 16 and a hook-shaped blade root 18.
  • the airfoil 14 is hollow and comprises at its first end 26 a feed side 34 for a cavity 28 can be supplied to the cooling medium K.
  • the feed side is only partially closed by a throttle element 36, since openings 38 are provided in the throttle element 36.
  • the openings 38 are arranged off-center, so that the minimum distance to the nearest side wall is substantially smaller than half of the distance H K of the two mutually opposite inner surfaces 21, 23rd
  • FIGS. 3, 4 show the usable for the turbine blades 10 throttle elements 36 with the openings 38 disposed therein in two embodiments.
  • the throttle element 36 has a plurality of openings 38, which have a circular flow cross-section.
  • the openings 38 are slot-shaped and curved in such a way that they follow the inner surfaces 21, 23 of the side walls 20, 22 to be cooled. Subsequently, the slot-shaped openings 38 are also referred to as slots 45.
  • the throttle elements 36 in the plan view of a sector-shaped shape.
  • this is only exemplary and not mandatory, since basically their shape depends on the shape of the cavity entrance in the cast turbine blade 10.
  • a center line 44 is defined, the points are each equidistant at a perpendicular distance to both inner surfaces 21, 23.
  • the openings 38 are arranged comparatively close to the inner surfaces 21, 23, ie the openings 38 are arranged eccentrically such that their opening cross-sections do not affect or intersect the center line 44.
  • the value for the mean distance H K for example, between 1 cm and 4 cm for the wall thickness WS of the throttle element, for example, between 0.5 mm and 2 mm.
  • the parameters should correspond to the values or conditions given in Table 2: Table 2: preferred values for an above-average cooled turbine blade.
  • Table 2 preferred values for an above-average cooled turbine blade.
  • H K set H K set WS set WS set a ⁇ 0.35 ⁇ H K a ⁇ 0.35 ⁇ H K d ⁇ 0.1 ⁇ H K s 0.1 ⁇ H K ⁇ s ⁇ 0.2 H K t ⁇ 0.25 d Z 1 ⁇ 0.25 d Z 1 ⁇ 1 ⁇ WS Z 2 ⁇ 0.25 d Z 2 ⁇ 0.5 WS
  • FIG. 5 is a further embodiment of a turbine blade 110 shown in fragmentary and purely schematic.
  • throttle element 136 is profiled so that its longitudinal section corresponds to the diagram after the longitudinal section through a cylinder hat.
  • the throttle element 136 is configured in the shape of a cylinder hatch and thus comprises a tubular section 137 whose first end is bounded by a cover 139 and at the second end opposite the first end a circumferential collar is provided.
  • the collar or the rim 141 serves for fastening the throttle element 136 to the remaining turbine blade 110.
  • the tubular section 137 extends into the cavity 128 with a length H.
  • Impact cooling openings 143 are provided in the tubular portion 137, the tubular portion being preferably not circular in cross-section, but the cross-sectional contour of the cavity 128 as seen in FIGS FIGS. 3 and 4 shown in dashed line form, resembles.
  • the area G of the airfoil is plumpable.
  • Circular openings 38 and slots 45 may be arranged above in order to make a region M of the airfoil convectively coolable, as seen downstream of region G in the flow direction of a cooling medium K.
  • Table 4 preferred values for an above-average cooled turbine blade with a hatch-shaped throttle element.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16153376.5A 2016-01-29 2016-01-29 Aube de turbine dotée d'un élément d'étranglement Withdrawn EP3199760A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16153376.5A EP3199760A1 (fr) 2016-01-29 2016-01-29 Aube de turbine dotée d'un élément d'étranglement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16153376.5A EP3199760A1 (fr) 2016-01-29 2016-01-29 Aube de turbine dotée d'un élément d'étranglement

Publications (1)

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EP3199760A1 true EP3199760A1 (fr) 2017-08-02

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EP16153376.5A Withdrawn EP3199760A1 (fr) 2016-01-29 2016-01-29 Aube de turbine dotée d'un élément d'étranglement

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944467A2 (fr) * 2007-01-11 2008-07-16 United Technologies Corporation Flux d' écoulement de circuit de refroidissement pour une section d' aube de turbine
EP2025868A1 (fr) * 2007-08-10 2009-02-18 Siemens Aktiengesellschaft Aube de turbine avec turbulateur à l'entrée d'air de refroidissement
WO2009153108A2 (fr) 2008-05-26 2009-12-23 Alstom Technology Ltd. Turbine à gaz pourvue d'une aube directrice
EP2628900A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Aube directrice de turbine dotée d'un élément d'étranglement
WO2013139926A1 (fr) * 2012-03-22 2013-09-26 Alstom Technology Ltd Aube de turbine
WO2014052744A1 (fr) * 2012-09-28 2014-04-03 United Technologies Corporation Refroidissement d'aube de turbine modulé
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944467A2 (fr) * 2007-01-11 2008-07-16 United Technologies Corporation Flux d' écoulement de circuit de refroidissement pour une section d' aube de turbine
EP2025868A1 (fr) * 2007-08-10 2009-02-18 Siemens Aktiengesellschaft Aube de turbine avec turbulateur à l'entrée d'air de refroidissement
WO2009153108A2 (fr) 2008-05-26 2009-12-23 Alstom Technology Ltd. Turbine à gaz pourvue d'une aube directrice
EP2628900A1 (fr) * 2012-02-14 2013-08-21 Siemens Aktiengesellschaft Aube directrice de turbine dotée d'un élément d'étranglement
WO2013139926A1 (fr) * 2012-03-22 2013-09-26 Alstom Technology Ltd Aube de turbine
WO2014052744A1 (fr) * 2012-09-28 2014-04-03 United Technologies Corporation Refroidissement d'aube de turbine modulé
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane

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