EP3088673B1 - Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés - Google Patents

Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés Download PDF

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Publication number
EP3088673B1
EP3088673B1 EP15165406.8A EP15165406A EP3088673B1 EP 3088673 B1 EP3088673 B1 EP 3088673B1 EP 15165406 A EP15165406 A EP 15165406A EP 3088673 B1 EP3088673 B1 EP 3088673B1
Authority
EP
European Patent Office
Prior art keywords
cavity
side wall
blade
gas turbine
squealer
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.)
Not-in-force
Application number
EP15165406.8A
Other languages
German (de)
English (en)
Other versions
EP3088673A1 (fr
Inventor
Fathi Ahmad
Christian Menke
Horst-Michael Dreher
Thorsten Mattheis
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 EP15165406.8A priority Critical patent/EP3088673B1/fr
Priority to US15/135,727 priority patent/US20160319675A1/en
Priority to CN201610269552.1A priority patent/CN106089315B/zh
Priority to JP2016088923A priority patent/JP6224161B2/ja
Publication of EP3088673A1 publication Critical patent/EP3088673A1/fr
Application granted granted Critical
Publication of EP3088673B1 publication Critical patent/EP3088673B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/186—Film 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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

Definitions

  • the invention relates to a rotor for a gas turbine, comprising a pressure-side wall and a suction-side wall, a tip cap, a cavity, which is formed by the inner surface of the pressure-side wall, the suction-side wall and the tip cap, and a squealer, extending radially from the pressure side and suction side wall, a half space formed by the outer surface of the tip cap and the squeal edge, and a cooling channel, which leads from the cavity to the squeal edge.
  • Blades of the above type are used in gas turbines to convert the energy of a hot gas stream into rotary energy. They typically have an airfoil traversed by one or more cavities for guiding cooling air, which has a pressure-side and a suction-side wall and is closed at its tip by a tip cap. On the tip cap a circumferential, in the radial direction (with respect to the axis of the gas turbine) extending squealer edge is often provided, which extends the pressure-side and suction-side wall in the radial direction.
  • Turbine blades are currently produced by casting from a single piece and a material. They are usually cooled during operation to protect the material of the blades from the high gas temperatures and to prevent their oxidation.
  • a proven and successful cooling design for turbine blades is the internal cooling. In this case flows a liquid or gaseous cooling fluid - usually air, which is taken from the compressor of the turbine - in the cavities described above.
  • the squeal edge described has relatively thin walls and is relatively far away from the cooling air inside the blade. For this reason, it is particularly susceptible to the high temperatures of the gas stream.
  • cooling channels pass from the cavity within the blade through the tip cap to the outside of the squeal edge. Cooling fluid exits through these cooling channels and thus cools the squealer edge.
  • Such an arrangement is for example from the EP 1 057 970 B1 known.
  • EP 1 267 041 B1 It is furthermore known to introduce into the inside, ie the side of the squealer edge facing the half-space, a cavity which interrupts the cooling channel. Although this improves the cooling effect. The disadvantage here is that this reduces the stability of the squealer. This limits the possible length of the cavity.
  • EP 1 557 533 A1 discloses the subject matter of the preamble of claim 1.
  • the tip cap has a cavity which extends from the half-space in the tip cap, that the cavity divides the cooling channel into a first part communicating with the cavity and communicating with the outside second part.
  • the invention is based on the consideration that an even longer life of the blade can be achieved, although a cooling channel interrupting the cavity is provided, but this does not reduce the stability of the squeal.
  • the cavity in the radial direction extends into the tip cap and thus does not reduce the thickness of the squealer.
  • the excavation reaches into the Cooling channels into it, which extend from the cavity within the blade to the outside of the squealer, so that these cooling channels are divided into a first and a second part.
  • the first part advantageously has an outlet opening in the cavity and / or the second part advantageously has an outlet opening on the outside of the squealer edge.
  • the cooling fluid flow from the cavity in the blade thus initially enters the cavity and thus cools the inside there in the half-space.
  • the cooling efficiency is very good here. Only then does it continue to flow through the second part to the outside of the squealer. Due to the prevailing in operation pressure differences in this case, no reversal of the current to be feared, d. H. no hot gas enters the half-space through the second part.
  • the blade of the cooling channel is formed linear. This applies to the entire cooling channel, d. H. first and second part lie on a common line. On the one hand, this enables a better flow of the cooling fluid out of the first into the second part of the cooling channel. On the other hand, but this allows a particularly simple introduction of the cooling channel, both the first and the second part in one piece, preferably by laser drilling. The laser is placed on the outside of the squealer and drills through the cavity into the cavity inside the blade.
  • the cavity extends in the manner of a groove along the pressure-side wall or along the suction-side wall of the blade.
  • a particularly homogeneous cooling is achieved because the cooling fluid from the cooling channel propagate along the groove length and evenly cool the squeal.
  • Particularly advantageous in terms of pressure conditions is an extension along the suction side wall.
  • a side wall of the cavity goes straight into the inside of the pressure-side or suction-side wall.
  • this enables a particularly simple casting mold, on the other hand, the cooling effect of the cooling fluid in the cavity or groove on the rubbing edge is thereby further improved.
  • the blade has, in an advantageous embodiment, a plurality of cooling channels leading from the cavity to the outside of the squealer, and the cavity divides the plurality of cooling channels into a respective first part communicating with the cavity and a second part communicating with the outer space.
  • the cooling channels are constructed identically. Through several cooling channels of this type, the cooling effect is further improved.
  • a rotor for a gas turbine advantageously comprises such a rotor blade.
  • a gas turbine advantageously comprises such a rotor.
  • a power plant advantageously comprises such a gas turbine.
  • the advantages achieved by the invention are in particular that by introducing a radial cavity in the tip cap, which divides the cooling channels to the outside of the squeal, a particularly good cooling effect is achieved with high stability of the squealer.
  • the cavity ensures that the cooling fluid outlet is ensured, despite possible casting deviations during the production of the blade.
  • the cooling fluid undergoes less pressure losses.
  • the life is also increased by the fact that in the half-space emerging cooling channels open into the cavity and are thus better protected against external hot gas.
  • FIG. 1 shows a plan view from a radially outer direction on a blade 1.
  • This has a pressure-side wall 2, a suction-side wall 4 and a tip cap 6 at the radial end of the blade 1.
  • a cooling fluid usually air taken from the compressor of the turbine - circulates within the cavity 18 and cools the pressure and suction side walls 2, 4 from the inside by convection.
  • the FIG. 1 in particular, shows the tip portion of the blade 1, which includes a squealer edge 8 and protects the tip portion of the blade from damage in the event of contact with the housing of the gas turbine.
  • the squeal edge 8 extends radially from the pressure and suction side wall 2, 4 in circumferentially same height.
  • the squealer 8 forms together with the tip cap 6 a half-space 10.
  • Several cooling channels 12 extend from the cavity within the blade through the squealer 8 up to the the outer space 14 facing side. This is in FIG. 1 not apparent and is still based on FIG. 2 clearer.
  • the cooling fluid flows through these cooling channels 12 and cools the squealer 8 by cooling from the inside.
  • the cooling fluid then exits the cooling channels 12 through the outlet openings 34 on the outside, cools the squealer 8 by flowing around the outside, and finally mixes with the leakage current of the gas turbine.
  • a cavity 16 is inserted, which extends in the radial direction inwardly and extending in a groove-like manner parallel to the suction-side wall 4.
  • the cavity 16 divides the cooling channels 12 in the vicinity of the suction-side wall 4. This will be described below with reference to FIG. 2 explained.
  • FIG. 2 shows the cross section along the line II of the tip portion of the blade 1 with the pressure side wall 2 and the suction side wall 4.
  • the cavity 18 in the blade 1 through the inner surfaces 20, 22 of the pressure and the suction side wall 2, 4th and the inner surface 24 of the tip cap 6 is formed.
  • a cooling channel 12 extends as described from the cavity 18 to the outside of the squealer 8. It is formed completely linear and introduced by means of laser drilling.
  • the cooling channel 12 is interrupted by the cavity 16 into a first part 28 which extends from the cavity 18 to an outlet opening 32 in the cavity 16 and into a second part 30 extending from the cavity 16 to the outlet opening 34 on the outside the squeal edge 8 extends.
  • FIG. 1 shown cooling channels 12 are identical and thus open into the cavity 16.
  • the cavity 16 is here formed with a rounded or curved side wall, which is most conveniently produced by casting.
  • FIG. 3 shows a rectangular cavity 16, which is most economically produced by a cutting shaping. Both forms are suitable from the standpoint of cooling fluid flow and the effectiveness of the cooling.
  • a side wall 36 of the cavity 16 just transitions into the inner side 38 of the squealer edge 8 on the suction-side wall 4.
  • FIG. 4 finally shows a gas turbine 100 in a longitudinal partial section.
  • a turbine is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular hot gas channel 111.
  • the turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed from two blade rings.
  • the hot gas channel 111 of a row of guide vanes 115 is followed by a row 125 formed of rotor blades 1.
  • the blades 120, 130 are profiled slightly curved, similar to an aircraft wing.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133.
  • the rotor blades 1 thus form components of the rotor or rotor 103. Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110. From there, the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 1.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 1 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the highest thermal load in addition to the heat shield bricks lining the annular combustion chamber 106.
  • the high loads make highly resilient materials necessary.
  • the turbine blades 1, 130 are therefore made of titanium alloys, nickel superalloy or tungsten-molybdenum alloys.
  • M Fe, Co, Ni, rare earths
  • thermal barrier coating for example ZrO2, Y2O4-ZrO2
  • TBC Thermal Barrier Coating
  • Other measures to make the blades more resistant to heat consist of sophisticated cooling duct systems. This technique is used both in the guide and in the rotor blades 1, 130.
  • Each vane 130 has a vane foot (also not shown), also referred to as a platform, facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the Leitschaufelkopf faces the rotor 103 and fixed to a sealing ring 140 of the stator 143.
  • Each sealing ring 140 encloses the shaft of the rotor 103.
  • each blade 1 has such a blade root, but ends in a blade tip. This is according to one in the 1 to FIG. 3 designed embodiment shown.

Landscapes

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

Claims (10)

  1. Aube (1) mobile d'une turbine (100) à gaz,
    comprenant un intrados (2) et un extrados (4), une coiffe (6) de pointe, une cavité (18) formée par la surface (20, 22, 24) intérieure de l'intrados (2), de l'extrados (4) et de la coiffe (6) de pointe, et un bord (8) d'attaque, qui s'étend radialement de l'intrados (2) à l'extrados (4), une demi-chambre (10), formée par la surface extérieure de la coiffe (6) de pointe et par le bord (8) d'attaque, et un conduit (12) de refroidissement, qui va de la cavité (18) au côté extérieur du bord (8) d'attaque, la coiffe (6) de pointe ayant un creux (16), le creux (16) subdivisant le conduit (12) de refroidissement en une première partie (28) communiquant avec la cavité (18), et en une deuxième partie (30) communiquant avec l'espace (14) extérieur,
    caractérisée en ce que
    la cavité (16) s'étend de la demi-chambre (10) à la coiffe (8) de pointe.
  2. Aube (1) mobile suivant la revendication 1,
    dans laquelle la première partie (28) a une ouverture (32) de sortie dans le creux (16).
  3. Aube (1) mobile suivant l'une des revendications précédentes,
    dans laquelle la deuxième partie (30) a une ouverture (34) de sortie du côté extérieur du bord (8) d'attaque.
  4. Aube (1) mobile suivant l'une des revendications précédentes,
    dans laquelle le conduit (12) de refroidissement est linéaire.
  5. Aube (1) mobile suivant l'une des revendications précédentes,
    dans laquelle le creux (16) s'étend, à la manière d'une rainure, le long de l'intrados (2) ou le long de l'extrados (4) de l'aube (1) mobile.
  6. Aube (1) mobile suivant la revendication 5,
    dans laquelle une paroi (36) latérale du creux (16) se transforme précisément en le côté (38) intérieur du bord (8) d'attaque.
  7. Aube (1) mobile suivant la revendication 5 ou 6,
    qui a plusieurs conduits (12) de refroidissement, qui vont de la cavité (18) au côté extérieur du bord (8) d'attaque, et
    dans laquelle le creux (16) subdivise les plusieurs conduits (12) de refroidissement en respectivement une première partie (28) communiquant avec la cavité (18) et respectivement une deuxième partie (30) communiquant avec l'espace (14) extérieur.
  8. Rotor (103) d'une turbine (100) à gaz,
    comprenant une aube (1) mobile suivant l'une des revendications précédentes.
  9. Turbine (100) à gaz, comprenant un rotor (103) suivant la revendication 8.
  10. Centrale électrique, comprenant une turbine (100) à gaz suivant la revendication 9.
EP15165406.8A 2015-04-28 2015-04-28 Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés Not-in-force EP3088673B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP15165406.8A EP3088673B1 (fr) 2015-04-28 2015-04-28 Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés
US15/135,727 US20160319675A1 (en) 2015-04-28 2016-04-22 Rotor blade for a gas turbine
CN201610269552.1A CN106089315B (zh) 2015-04-28 2016-04-27 用于燃气涡轮的转子叶片
JP2016088923A JP6224161B2 (ja) 2015-04-28 2016-04-27 ガスタービンのためのロータブレード

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15165406.8A EP3088673B1 (fr) 2015-04-28 2015-04-28 Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés

Publications (2)

Publication Number Publication Date
EP3088673A1 EP3088673A1 (fr) 2016-11-02
EP3088673B1 true EP3088673B1 (fr) 2017-11-01

Family

ID=53002624

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15165406.8A Not-in-force EP3088673B1 (fr) 2015-04-28 2015-04-28 Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés

Country Status (4)

Country Link
US (1) US20160319675A1 (fr)
EP (1) EP3088673B1 (fr)
JP (1) JP6224161B2 (fr)
CN (1) CN106089315B (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9618002B1 (en) * 2013-09-27 2017-04-11 University Of South Florida Mini notched turbine generator

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62223402A (ja) * 1986-03-24 1987-10-01 Toshiba Corp タ−ビン動翼の先端冷却構造
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
US6231307B1 (en) * 1999-06-01 2001-05-15 General Electric Company Impingement cooled airfoil tip
US6164914A (en) * 1999-08-23 2000-12-26 General Electric Company Cool tip blade
US6341939B1 (en) * 2000-07-31 2002-01-29 General Electric Company Tandem cooling turbine blade
US6527514B2 (en) * 2001-06-11 2003-03-04 Alstom (Switzerland) Ltd Turbine blade with rub tolerant cooling construction
US20030021684A1 (en) * 2001-07-24 2003-01-30 Downs James P. Turbine blade tip cooling construction
US6994514B2 (en) * 2002-11-20 2006-02-07 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
EP1557533B1 (fr) * 2004-01-23 2008-03-12 Siemens Aktiengesellschaft Refroidissement d'une aube de turbine avec faux-plancher entre l'aube et son extrémité
US7287959B2 (en) * 2005-12-05 2007-10-30 General Electric Company Blunt tip turbine blade
US7695243B2 (en) * 2006-07-27 2010-04-13 General Electric Company Dust hole dome blade
CN102182518B (zh) * 2011-06-08 2013-09-04 河南科技大学 一种涡轮冷却叶片
FR2983517B1 (fr) * 2011-12-06 2013-12-20 Snecma Aube de turbine refroidie pour moteur a turbine a gaz.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US20160319675A1 (en) 2016-11-03
JP2016211556A (ja) 2016-12-15
EP3088673A1 (fr) 2016-11-02
CN106089315B (zh) 2018-08-31
CN106089315A (zh) 2016-11-09
JP6224161B2 (ja) 2017-11-01

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