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
• • 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
  • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
  • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
  • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
• • 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
  • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/20—Heat transfer, e.g. cooling
  • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
• • 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
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to an axial rotor section for a rotor of a gas turbine with an outer peripheral surface adjoining two end-side first side surfaces, in which circumferentially distributed, along an axial direction extending blade holding slots for blades of the turbine are provided. Furthermore, the invention relates to a turbine blade with a blade root, an adjoining platform and located on the side facing away from the foot platform of the platform, wherein in
• Blade foot is provided at least one opening for supplying a coolant into the turbine blade inner, which merges into a coolant channel.
• a generic axial rotor section for a turbine is known for example from the published patent application DE 1 963 364 AI.
• the rotor section formed by a rotor disk is equipped with holding grooves extending in the axial direction for rotor blades of the turbine, wherein an end-to-end receiving groove for sealing plates is provided on the front side.
• the seated therein sealing plates block a displacement of the blades along the retaining and thus fix them.
• Each sealing sheet is thereby from a
• the sealing plates also form a sealing ring when viewed in the circumferential direction.
• the sealing ring separates a first space between the sealing plate and the end face of the rotor disk from a second space lying beyond the sealing plate.
• the first space is traversed by cooling air, which prevents thermal overload of the blade root and the outer edge of the rotor disk.
• a disadvantage of the known device is the use of a screw to secure the sealing plates against displacement in the circumferential direction. Due to the thermal cycling occurring between operation and standstill and due to the hot gas flowing through the turbine, corrosion and strength problems in the fitting may occur. Under certain circumstances, this can not be solved as intended.
• a rotor assembly for a rotor disc of a turbine which has a one-piece sealing ring for axial securing of blades. Due to the one-piece sealing ring but this is only suitable for aircraft gas turbines, since they are assembled in the axial direction by alternately stacking rotor and stator components. Stationary gas turbines, on the other hand, are composed of two housing halves that surround the fully assembled rotor.
• the one-piece sealing ring of DE 30 33 768 A1 is connected to the turbine disk in the manner of a bayonet closure.
• a generic gas turbine blade with a blade root, a platform and an airfoil known.
• the platform extends from an upstream edge to a downstream edge relative to the hot gas flowing through the gas turbine in the axial direction.
• the platform has an outflow-side edge extending in the circumferential direction of the turbine disk, which protrudes beyond the axial width of the turbine disk in the manner of a eaves.
• the cooling air flow influencing structural elements are provided at the bottom of the downstream edge of the platform several.
• the object of the invention is therefore to provide a turbine blade and an axial rotor section, with which the aforementioned requirements can be met.
• a number of outlet holes are provided for cooling adjacent components, which open into the respective coolant channel.
• the invention is based on the finding that the fairlead of the turbine bucket can also be used for other purposes than carrying the platform and the adjoining airfoil.
• the blade root of the turbine blade is designed so that it becomes part of a cooling arrangement, wherein the component to be cooled does not belong to the turbine blade, but is a sealing element, which are adjacent to each other in the installed state.
• the sealing element fixes the relevant turbine blade in the blade retaining groove axially and to In addition, it directs a coolant near the surface of a side surface of an axial rotor portion and on the end face of the blade root. At the same time, this coolant flow bypassed so far also cooled the sealing element.
• a supply channel the coolant channel
• the impingement coolant which preferably extends comparatively close below the end face of the blade root.
• the coolant channel extends in the radial direction.
• a number of holes in the end face of the blade root are provided, which open in the coolant channel. The coolant flowing in the coolant channel can then radiate out through the holes, the so-called outlet holes, on the end face of the blade root, after which it impinges on the surface of the sealing element facing the end face of the blade root.
• the longitudinal axes of the outlet holes can have any required angle with respect to the longitudinal extent of the blade root or of the rotor blade groove, in order to chill the largest possible area of the sealing element.
• Another advantage is the increased sealing effect in the blade system, since less cooling air flows along the side surface of the rotor section due to the impingement cooling jets. If sealing elements are provided on the axial rotor section of the gas turbine at both end faces of the blade root, the use of the device according to the invention with coolant channels and outlet holes arranged on the front side likewise offers itself on both end sides of the blade root. Both the coolant channel and the frontally arranged outlet holes can be produced directly during the casting of the blade root or the turbine blade.
• the coolant channel and / or the outlet holes can be done, for example, by means of laser drilling or by erosion. Expediently, the outlet holes are distributed in a uniform grid surface.
• Other manufacturing methods for example the fastening of a baffle-cooling plate above an end-side coolant channel groove, are also conceivable.
• At least one spacer may be provided on the relevant end face.
• the opening of the coolant channel is arranged on blade bottom and between the opening and the associated end face of the blade root for the coolant pressure loss generating element or a sealing element blade bottom is arranged.
• the pressure gradient can be adjusted so that the coolant flows into the coolant channel and flows out through the outlet holes.
• these elements need not necessarily be integrally formed with the blade or with the axial rotor section. They can also be designed as a separately produced seal or flow barrier.
• FIG 2 shows the cross-sectional view of FIG 1 along the
• FIG. 3 shows a longitudinal section through the foot region of a turbine blade according to the invention
• 4 shows a perspective view of the blade root of the turbine blade according to the invention.
• FIG. 1 shows an axial rotor section 10 in a side view and FIG. 2 in a cross section according to section line II-II from FIG. 1.
• Each sealing element 16 is seated with its radially inner end 18 in a groove 20 provided on a rotor disk 19 at the front and with its radially outer end 22 in a securing groove 24 which is provided on the underside 26 of a platform 28 of the rotor blade 14.
• a radially rectilinear sheet metal strip 30 is attached to each.
• Each sheet metal strip 30 terminates at its radially outer end 32 in a uniformly converging point 34.
• Chamfered edges 36 are provided on the platforms 28 of the rotor blades 14, two opposite edges 36 of immediately adjacent rotor blades 14 forming a tapered recess 38, respectively in which the tip 34 of the metal strip 30 for securing the sealing element 16 protrude against a shift in the circumferential direction U and can rest.
• the sealing elements 16 also ensure a separation of two spaces 37, 39, in which on the one hand coolant and on the other hand a mixture of coolant and hot gas flow can occur.
• two parallel slots 40 are provided in the latter, by the already U-shaped pre-bent sheet metal strip 30 is used.
• the end 41 of the sheet-metal strip 30 lying opposite the tip 34 is already bent before the assembly of the sealing element 16 on the rotor disk 19 into the position shown in FIG. 2 for fastening the sheet-metal strip 30.
• the sealing elements 16 with the preassembled metal strips 30 are successively threaded into the endless circumferential groove 20 arranged on the rotor disk 19 and into the securing groove 24 arranged on the underside 26 of the platform 28.
• the sealing elements 16 are positioned along the circumference of the groove 20 so that each sheet metal strip 30 faces a recess 38. Subsequently, the tips 34 of the sheet metal stiffeners 30 are bent into the recesses 38 in order to preclude a displacement of the sealing elements 16 in the circumferential direction U.
• exit holes 58 are provided in an end face 52 of the blade root 54 and in the side surfaces 53 of so-called claws 56, which form the outer edge of the rotor disc 19 between two directly adjacent retaining grooves 12.
• the outlet holes 58 arranged in the blade root 54 are connected to a coolant channel 60 whose inlet-side opening 62 for supplying a coolant is arranged in the underside 64 of the blade root 54.
• coolant 66 flows through a cooling channel 65 arranged in the rotor disk into the free space 67 between the blade foot bottom 64 and the groove bottom of the retaining groove 12.
• the coolant 66 From there, part of the coolant 66 reaches the opening 62, whereupon it then enters the coolant channel 60. Due to the existing pressure gradient, the coolant 66 then flows through the outlet holes 58 in Form of impingement cooling jets and impinges bouncing on the sealing element 16th
• a pressure loss-generating element 68 on the underside 64 of the blade root 54 between opening 62 and end face 52. This can also be designed as a sealing element. For a defined distance between end face 52 of the
• Shovel 54 and sealing element 16 may be provided on the front side 52 and a spacer 70.
• the supply of arranged in the claws 56 outlet holes 58 with cooling air can be achieved by means of suitable holes (not shown) in the rotor disk 19.
• FIGs 3 and 4 show the turbine blade 14 according to the invention comprising the blade root 54, a platform 28 and arranged thereon the blade 15, the latter, however, is only partially shown. Furthermore, the supply port 62 and the exit holes 58 are shown. The distance between the end face 52 of the blade root 54 and the opening 62 is comparatively small, so that the coolant channel 60 shown in cross section in FIG. 3 is arranged comparatively close to the end face 52 assigned to it. The coolant channel 60 extends parallel to the substantially planar end face 52 of the blade root 54.
• the invention thus relates to a turbine blade 14 having a blade root 54, an adjoining platform 28 and a remote from the blade root 54 side of the platform 28 airfoil 15, wherein at an underside 64 of the blade root 54 at least one opening 62 for supplying a Coolant 66 is provided in the turbine blade inner, which merges into a coolant channel 60.
• the invention relates an axial rotor section 10 for a rotor 23 of a turbine, having an outer peripheral surface adjacent to two frontal side surfaces 53, in which circumferentially distributed, axially extending blade containment slots 12 for turbine blades 14 are provided, each retaining groove 12 a turbine blade 14 is arranged, wherein the side of a side surface 53 of the rotor portion 10, a plurality of sealing elements 16 are provided, the gap forming the end faces 52 of the blade roots 54 opposite.
• a multiplicity of outlet holes 58 are provided in the side face 53 and / or in the end face 52 for impingement cooling of the sealing elements 16.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=48182893

Family Applications (1)

Country Status (7)

Families Citing this family (9)

Family Cites Families (23)

• 2013
  • 2013-04-15 IN IN8366DEN2014 patent/IN2014DN08366A/en unknown
  • 2013-04-15 EP EP13718314.1A patent/EP2823152A1/de not_active Withdrawn
  • 2013-04-15 WO PCT/EP2013/057753 patent/WO2013167346A1/de active Application Filing
  • 2013-04-15 JP JP2015510703A patent/JP5990639B2/ja not_active Expired - Fee Related
  • 2013-04-15 US US14/398,464 patent/US9745852B2/en not_active Expired - Fee Related
  • 2013-04-15 RU RU2014149236A patent/RU2014149236A/ru not_active Application Discontinuation
  • 2013-04-15 CN CN201380024454.6A patent/CN104285040B/zh not_active Expired - Fee Related

Non-Patent Citations (2)

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