US20110038733A1 - Blade for a rotating thermal machine - Google Patents

Blade for a rotating thermal machine Download PDF

Info

Publication number
US20110038733A1
US20110038733A1 US12/892,555 US89255510A US2011038733A1 US 20110038733 A1 US20110038733 A1 US 20110038733A1 US 89255510 A US89255510 A US 89255510A US 2011038733 A1 US2011038733 A1 US 2011038733A1
Authority
US
United States
Prior art keywords
blade
angle
airfoil
trailing edge
stator
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.)
Abandoned
Application number
US12/892,555
Other languages
English (en)
Inventor
Willy Heinz Hofmann
Michael Huber
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Assigned to ALSTOM TECHNOLOGY LTD. reassignment ALSTOM TECHNOLOGY LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HOFMANN, WILLY HEINZ, HUBER, MICHAEL
Publication of US20110038733A1 publication Critical patent/US20110038733A1/en
Abandoned legal-status Critical Current

Links

Images

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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/304—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 trailing edge 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the present disclosure relates to the field of thermal machines. More particularly, the present disclosure relates to a blade for a rotating thermal machine.
  • FIG. 1 shows a known gas turbine 10 with sequential combustion, in which a compressor 11 , a first combustion chamber 14 , a high-pressure (HP) turbine 15 , a second combustion chamber 17 and a low-pressure (LP) turbine 18 are arranged in series along an axis 19 .
  • the compressor 11 and the two turbines 15 (HP), 18 (LP) are part of a rotor which rotates around the axis 19 .
  • the compressor 11 compresses the inducted air, and this compressed air then flows into a plenum and from there flows into the first combustion chamber 14 .
  • the first combustion chamber 14 is operated with premix burners, as described in, for example, EP-A1-0 321 809 and EP-A2-0 704 657.
  • the compressed air flows into the premix burners in which the compressed air is mixed with at least one fuel.
  • This fuel/air mixture then flows into the first combustion chamber 14 in which this mixture is combusted, forming a stable flame front.
  • the resulting hot gas is partially expanded in the adjoining high-pressure turbine 15 , performing work, and then flows into the second combustion chamber 17 in which a further fuel feed 16 takes place.
  • combustion takes place in the second combustion chamber 17 , which is based on self-ignition.
  • the hot gas which is reheated in the second combustion chamber 17 is then expanded in the multistage low-pressure turbine 18 in which blade rows including rotor blades and stator blades are arranged one behind the other in an alternating manner.
  • the low-pressure turbine 18 includes a blading 29 in which a plurality of rows of rotor blades and stator blades are arranged one behind the other and in an alternating manner in the flow direction.
  • the stator blades have a blade airfoil 22 (see FIG. 2 ) which extends in the radial direction between a shroud 21 (see FIG. 2 ) and a blade tip 23 (see FIG. 2 ).
  • the shroud 21 and blade tip 23 constitute two ends of the stator blade.
  • the above-described construction of the stator blade also applies to the rotor blades.
  • the two ends 21 , 23 of the stator blade delimit the throughflow cross section of a hot gas passage in the radial direction, through which passage a hot gas flow 30 (see FIG. 2 ) flows and impinges upon the blade airfoil 22 of the blade with corresponding flow lines, of which three flow lines are exemplarily shown in FIG. 2 and designated with reference symbol 26 .
  • the throughflow cross section of the hot gas passage widens considerably in the flow direction, conforming to the turbine 10 .
  • certain consequences arise for the geometric design of the respective blade airfoil.
  • the blade airfoils of stator blades in gas turbines or steam turbines are customarily designed so that the local flow lines of the flowing operating medium (hot gas or steam) at the point of intersection with the trailing edge of the blade airfoil extend approximately perpendicularly to the trailing edge.
  • the trailing edge On account of the large angle of inclination of the flow path in the meridional plane, the trailing edge, however, cannot be oriented completely and continuously perpendicularly to the flow lines because this would require a sharp sweep angle and tilt, for example, at the blade tip which, however, is not possible, on account of the given space conditions and assembly, apart from the fact that such a configuration, even if this were able to be accomplished, would otherwise have fluidic disadvantages.
  • An exemplary embodiment provides a blade for a rotating thermal machine.
  • the exemplary blade includes a blade airfoil which extends essentially in a radial direction, is exposed to circumflow by an operating medium in a flow direction, and is delimited by a leading edge and a trailing edge in the flow direction.
  • the blade airfoil is structured such that an angle which flow lines of the operating medium form with a shape of the trailing edge of the blade airfoil deviates within a limited range from a 90°-angle.
  • FIG. 1 shows a basic construction of a known gas turbine with sequential combustion
  • FIG. 2 shows in a perspective side view a stator blade, such as one which can be used in a gas turbine according to FIG. 1 , and also shows features of a stator blade according to an exemplary embodiment of the present disclosure;
  • FIG. 3 shows the deviation of an angle, which the flow lines form with the trailing edge of a blade which is comparable to FIG. 2 , from the right angle over the height of the blade if the blade has a fully orthogonal “stacking”, according to an exemplary embodiment of the present disclosure
  • FIG. 4 shows the deviation of an angle, which the flow lines form with the trailing edge of the blade which is shown in FIG. 2 , from the right angle over the height of the blade, according to an exemplary embodiment of the present disclosure.
  • Exemplary embodiments of the present disclosure provide a blade which has a fluidically optimum body shape inside a prespecified throughflow cross section. This exemplary arrangement can provide a maximized efficiency.
  • Exemplary embodiments of the present disclosure provide an improved shape of the blade airfoil, in which the angle which the flow lines form with the trailing edge of the blade airfoil deviate from a right angle within a limited range, as would ensue in the case of a constant throughflow cross section.
  • the angle which the flow lines therefore form with the trailing edge of the blade airfoil can be, for example, less than 90°. In some cases, the angle can also be more than 90°.
  • the deviation with regard to this angle which the flow lines form with the trailing edge of the blade airfoil lies within the range of between 0° and ⁇ 10° or +10° in comparison to a right angle.
  • the deviation of the angle which the flow lines form with the trailing edge of the blade airfoil can lie within the range of between 0° and ⁇ 5°, and/or between 0° and +5°, over the largest area of the height of the blade airfoil.
  • the deviations within the angle range are not uniform over the entire length of the blade airfoil.
  • the flow lines do not have a deviation by the same amount within specific flow sections along the length of the blade airfoil in each case.
  • An oscillating deviation within the applied angle range along the entire length of the blade airfoil is also possible.
  • FIG. 2 shows an example of a stator blade, which can be used in a turbine of a gas turbine generator set, for example, in the low-pressure turbine of a gas turbine with sequential combustion according to FIG. 1 .
  • the stator blade 20 includes a blade airfoil 22 which is comparatively sharply curved in space.
  • the blade airfoil extends in the longitudinal direction (in the radial direction in relation to the rotor of the gas turbine) between a blade tip 23 and a shroud 21 , and extends from a leading edge 27 to a trailing edge 28 in the throughflow direction (flow direction) of the hot gas flow 30 .
  • the blade airfoil 22 is outwardly delimited by a suction side 31 and a pressure side opposite to the suction side 31 .
  • the hot gas flow 30 flows from the leading edge 27 to the trailing edge 28 along the blade airfoil 22 in flow lines 26 .
  • Three such flow lines 26 are exemplarily shown in FIG. 2 .
  • the flow lines 26 form an angle ⁇ at their point of intersection with the trailing edge 28 in each case.
  • the angle ⁇ varies in the radial direction and thus has a dependency upon the height h of the blade airfoil 22 .
  • this fully orthogonal stacking is replaced by a less strict “relaxed orthogonal stacking”, in which the angle ⁇ indeed stays close to a right angle but can deviate from this within a limited range.
  • the diagram corresponding to FIG. 3 for such a “relaxed” orthogonal stacking is reproduced in FIG. 4 .
  • the deviation ⁇ -90° of the angle ⁇ from the right angle lies within the negative range ( ⁇ 0) and overall is limited to an angle range of between 0 and ⁇ 10° in the currently shown example.
  • the deviation begins with a maximum value of almost ⁇ 10°, then returns to zero within a very short distance, and in the currently shown example remains below ⁇ 5° over the largest area of the height.
  • a limited deviation of this type from the strict orthogonal stacking at the same time can meet the fluidic, constructional and space-dependent demands on the blade inside a varying throughflow cross section, including maximizing the efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/892,555 2008-03-28 2010-09-28 Blade for a rotating thermal machine Abandoned US20110038733A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH4672008 2008-03-28
CH00467/08 2008-03-28
PCT/EP2009/052533 WO2009118234A1 (de) 2008-03-28 2009-03-04 Schaufel für eine rotierende thermische maschine

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/052533 Continuation WO2009118234A1 (de) 2008-03-28 2009-03-04 Schaufel für eine rotierende thermische maschine

Publications (1)

Publication Number Publication Date
US20110038733A1 true US20110038733A1 (en) 2011-02-17

Family

ID=39870460

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/892,555 Abandoned US20110038733A1 (en) 2008-03-28 2010-09-28 Blade for a rotating thermal machine

Country Status (3)

Country Link
US (1) US20110038733A1 (de)
EP (1) EP2268900A1 (de)
WO (1) WO2009118234A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106979177A (zh) * 2016-01-18 2017-07-25 通用电气公司 涡轮压缩机导叶
US9957645B2 (en) 2013-12-23 2018-05-01 Cytec Industries Inc. Method for producing carbon fibers from polyacrylonitrile (PAN) polymers with low polydispersity index (PDI)
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US850200A (en) * 1905-11-28 1907-04-16 Gen Electric Turbine bucket and nozzle.
US4433955A (en) * 1981-03-26 1984-02-28 General Electric Company Turbine arrangement
US4714407A (en) * 1984-09-07 1987-12-22 Rolls-Royce Plc Aerofoil section members for turbine engines
US4932861A (en) * 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
US5342170A (en) * 1992-08-29 1994-08-30 Asea Brown Boveri Ltd. Axial-flow turbine
US5454220A (en) * 1993-04-08 1995-10-03 Abb Management Ag Method of operating gas turbine group with reheat combustor
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US6099248A (en) * 1997-11-17 2000-08-08 Abb Alstom Power (Switzerland) Ltd Output stage for an axial-flow turbine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2899128A (en) * 1959-08-11 Vaghi

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US850200A (en) * 1905-11-28 1907-04-16 Gen Electric Turbine bucket and nozzle.
US4433955A (en) * 1981-03-26 1984-02-28 General Electric Company Turbine arrangement
US4714407A (en) * 1984-09-07 1987-12-22 Rolls-Royce Plc Aerofoil section members for turbine engines
US4932861A (en) * 1987-12-21 1990-06-12 Bbc Brown Boveri Ag Process for premixing-type combustion of liquid fuel
US5342170A (en) * 1992-08-29 1994-08-30 Asea Brown Boveri Ltd. Axial-flow turbine
US5454220A (en) * 1993-04-08 1995-10-03 Abb Management Ag Method of operating gas turbine group with reheat combustor
US5588826A (en) * 1994-10-01 1996-12-31 Abb Management Ag Burner
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
US6099248A (en) * 1997-11-17 2000-08-08 Abb Alstom Power (Switzerland) Ltd Output stage for an axial-flow turbine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9957645B2 (en) 2013-12-23 2018-05-01 Cytec Industries Inc. Method for producing carbon fibers from polyacrylonitrile (PAN) polymers with low polydispersity index (PDI)
US10189985B2 (en) 2013-12-23 2019-01-29 Cytec Industries Inc. Polyacrylonitrile (PAN) polymers with low polydispersity index (PDI) and carbon fibers made therefrom
US10647844B2 (en) * 2013-12-23 2020-05-12 Cytec Industries Inc. Polyacrylonitrile (PAN) polymers with low polydispersity index (PDI) and carbon fibers made therefrom
CN106979177A (zh) * 2016-01-18 2017-07-25 通用电气公司 涡轮压缩机导叶
EP3196409A3 (de) * 2016-01-18 2017-08-23 General Electric Company Turbinenverdichterleitschaufel
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge
US11629599B2 (en) 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge

Also Published As

Publication number Publication date
WO2009118234A1 (de) 2009-10-01
EP2268900A1 (de) 2011-01-05

Similar Documents

Publication Publication Date Title
US9726021B2 (en) High order shaped curve region for an airfoil
JP6650687B2 (ja) ロータブレード冷却
US8439626B2 (en) Turbine airfoil clocking
EP2716865A1 (de) Abgasdiffusor
US9759076B2 (en) Airfoil shape for a compressor
US20100054929A1 (en) Turbine airfoil clocking
US9745994B2 (en) Airfoil shape for a compressor
US9777744B2 (en) Airfoil shape for a compressor
US9732761B2 (en) Airfoil shape for a compressor
US9759227B2 (en) Airfoil shape for a compressor
US9938985B2 (en) Airfoil shape for a compressor
US20110038733A1 (en) Blade for a rotating thermal machine
US9746000B2 (en) Airfoil shape for a compressor
US20170067357A1 (en) Airfoil shape for a compressor
US20170067482A1 (en) Airfoil shape for a compressor
WO2017105260A1 (en) Blade and corresponding turbomachine
US9957964B2 (en) Airfoil shape for a compressor
CN111608735B (zh) 翼及具备该翼的机械
CN108999647B (zh) 涡轮机转子叶片
EP3372786B1 (de) Hochdruckverdichterrotorschaufel mit vorderkante mit einkerbungssegment
EP3828386B1 (de) Turbomaschinenrotorschaufel mit variabler elliptischer hinterkante
EP3828390A1 (de) Turbomaschinendüse mit einem profil mit einer gekrümmten hinterkante
EP3889392A1 (de) Turbomaschinenrotorschaufel mit einem kühlkreislauf mit versetzter rippe
US11415012B1 (en) Tandem stator with depressions in gaspath wall
EP4144959A1 (de) Strömungmaschine für ein flugzeugtriebwerk und flugzeugtriebwerk

Legal Events

Date Code Title Description
AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD., SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:HOFMANN, WILLY HEINZ;HUBER, MICHAEL;SIGNING DATES FROM 20101014 TO 20101018;REEL/FRAME:025232/0803

STCB Information on status: application discontinuation

Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION