EP1223308A2 - Refroidissement d'une composante d'une turbomachine - Google Patents

Refroidissement d'une composante d'une turbomachine Download PDF

Info

Publication number: EP1223308A2
Authority: EP; European Patent Office
Prior art keywords: channel; flow; cooling; deflection; section
Prior art date: 2000-12-16
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.): Granted

Application number

EP01129169A

Other languages

German (de)

English (en)

Other versions

EP1223308A3 (fr

EP1223308B1 (fr

Inventor

Sacha Parneix

Martin Dr. Schnieder

Jens Prof. Dr. Von Wolfersdorf

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.)

GE Vernova GmbH

Original Assignee

Alstom Technology AG

Alstom Schweiz 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.)

2000-12-16

Filing date

2001-12-08

Publication date

2002-07-17

2001-12-08 Application filed by Alstom Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG

2002-07-17 Publication of EP1223308A2 publication Critical patent/EP1223308A2/fr

2004-01-02 Publication of EP1223308A3 publication Critical patent/EP1223308A3/fr

2007-01-24 Application granted granted Critical

2007-01-24 Publication of EP1223308B1 publication Critical patent/EP1223308B1/fr

2021-12-08 Anticipated expiration legal-status Critical

Status Expired - Lifetime 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
- F01D5/12—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

Definitions

the present invention relates to a component a turbomachine, in particular a turbine blade, which can be flowed through by a cooling medium Cooling channel with at least one through the wall of the cooling channel formed deflection through which the flow of the cooling medium from a first Canal section into a downstream second Channel section is deflected, being in the area of Deflecting at least one flow guiding element in the Cooling channel is arranged through which the cooling channel in the diversion into an inner and an outer Flow channel is divided.
a separate cooling duct 2a is additionally provided, via which part of the cooling air is guided to the front and tip of the blade in order to exit there via corresponding openings 4.
the flow pattern of the cooling air within the airfoil is indicated by the arrows.
180 ° deflections 5 are required in the vicinity of the blade tip or the blade root, which connect the different sections of the cooling air duct 2 to one another.
complicated flow patterns with dead water areas develop, which lead to large pressure losses over the length of the cooling air duct 2 and thus require an increased pumping capacity for the transport of the cooling air.
the task is performed using the component Claim 1 solved.
Advantageous configurations the component are the subject of the subclaims.
the proposed solution is therefore a Reduction of pressure losses in the redirection simultaneous homogenization of the heat transfer between the cooling medium and the wall material of the Component reached.
the present design is regardless of the further configuration of the Component, in particular regardless of the rib configuration in the first and second channel section, in Hereinafter also referred to as the inlet and outlet duct, as well as possible curves on the outer Edge areas of the deflection. Such details, that with a variety of gas turbine blades occur do not affect the beneficial Effect of the present invention.
the drilling leads to the dissolution of the dead water areas and thus contributes to a homogenization of the heat transfer. Furthermore, these bores can bring about the desired side effect that dust particles in the cooling medium are blown out through the bores. To reinforce this side effect, the longitudinal axes of the bores are aligned approximately in the direction of the local streamlines of the flow of the cooling medium in the cooling channel. Due to the low adjacent flow velocity, the additional bores only make a small contribution to the global pressure loss via the cooling channel, which, due to the advantageous effect mentioned above, is hardly noticeable to minimize the pressure loss.
the thickness of the partition wall increases in the region of the deflection, in order to reduce the corresponding constriction within the region due to this increase in thickness inner flow channel.
the shape of the contour of this partition wall, which separates the outlet duct from the inlet duct, can be different in order to bring about the effect mentioned.
the flow guide element is preferably such trained and arranged within the deflection, that about 25 to 45% of the mass flow from the Inlet channel into the flow entering the deflection the area within the flow guide element, i.e. into the inner flow channel, enters and the rest outside the baffle, i.e. in the outer flow channel, flows.
the mass flow ratio corresponds to that Entry cross-sectional area ratio of the outer and inner flow channel.
the area ratio on The outlet duct should be roughly the same as the inlet duct correspond, i.e. it shouldn't be more than 20% deviate from this ratio.
the round baffle vary in thickness, or even again with Guide devices should be provided.
FIG. 3 shows a schematic representation Embodiment for the design of the cooling channel deflection 5 the component of a turbomachine according to the present invention.
the flow direction of the cooling medium is in turn through in this figure thick arrows indicated.
the cooling medium overflows a first channel section 9 in the deflection 5 and thence to a second canal section 10.
the two Channel sections 9 and 10 are used in this example separated from each other by a partition 11, the Is part of the cooling channel wall 12.
Such one Cooling channel can be in a usual gas turbine blade, as shown for example in FIG. 1, be arranged.
the deflection baffle is designed such that approximately 25 to 45% of the mass flow of the flow entering the deflection 5 from the inlet duct 9 flows into the area of the inner flow channel 13 and the rest flows into the area of the outer flow channel 14.
the mass flow ratio corresponds to the inlet area ratio A '/ B'.
the area ratio at the outlet duct A "/ B" in this example corresponds to the area ratio at the inlet duct and should not deviate more than ⁇ 20% from A '/ B'.
the holes 15 depending on location with its axis of drilling approximately in Direction of the streamlines of the flow of the cooling medium aligned so that - as an additional side effect - the discharge of small particles or dust in the Cooling air can take place via the bores 15.
FIG. 5 shows another preferred Embodiment of the invention shown in Figure 3.
the flow guide element 8 has a number of bores 16, which contribute to dust and Dirt accumulation in the outer 14 or inner 13 Avoid flow channel.
Figure 6 shows another Possibility to achieve this effect.
the Flow guide element is in several sub-elements, 8a and 8b, divided between which a gap is trained, which has the same effect as the bores 16 in FIG. 5.

Landscapes

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

EP01129169A 2000-12-16 2001-12-08 Composante d'une turbomachine Expired - Lifetime EP1223308B1 (fr)

Applications Claiming Priority (4)

Application Number	Priority Date	Filing Date	Title
DE10062906		2000-12-16
DE10062906		2000-12-16
DE10126215		2001-05-30
DE10126215		2001-05-30

Publications (3)

Publication Number	Publication Date
EP1223308A2 true EP1223308A2 (fr)	2002-07-17
EP1223308A3 EP1223308A3 (fr)	2004-01-02
EP1223308B1 EP1223308B1 (fr)	2007-01-24

Family

ID=26007995

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP01129169A Expired - Lifetime EP1223308B1 (fr)	2000-12-16	2001-12-08	Composante d'une turbomachine

Country Status (3)

Country	Link
US (1)	US6595750B2 (fr)
EP (1)	EP1223308B1 (fr)
DE (1)	DE50111949D1 (fr)

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EP1456505A1 (fr) *	2001-12-10	2004-09-15	ALSTOM Technology Ltd	Piece a sollicitation thermique
EP1607576A2 (fr)	2004-06-14	2005-12-21	United Technologies Corporation	Passage coudé de refroidissement d'aile et méthode de fabrication
WO2007050205A3 (fr) *	2005-09-19	2007-09-20	United Technologies Corp	Echangeur thermique compact
WO2009118245A1 (fr) *	2008-03-28	2009-10-01	Alstom Technology Ltd	Aube directrice pour turbine à gaz et turbine à gaz dotée d'une aube directrice de ce type
US8985940B2 (en)	2012-03-30	2015-03-24	Solar Turbines Incorporated	Turbine cooling apparatus
WO2016148690A1 (fr) *	2015-03-17	2016-09-22	Siemens Energy, Inc.	Aube de turbine avec structure de guidage tournante à écoulement sans contrainte

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US6939102B2 (en) *	2003-09-25	2005-09-06	Siemens Westinghouse Power Corporation	Flow guide component with enhanced cooling
US7377747B2 (en) *	2005-06-06	2008-05-27	General Electric Company	Turbine airfoil with integrated impingement and serpentine cooling circuit
US7445432B2 (en) *	2006-03-28	2008-11-04	United Technologies Corporation	Enhanced serpentine cooling with U-shaped divider rib
TWI448285B (zh)	2006-07-13	2014-08-11	Los Angeles Biomed Res Inst	用以治療白黴菌症（ｍｕｃｏｒｍｙｃｏｓｉｓ）及其他真菌類疾病之組合物及方法
US7625178B2 (en) *	2006-08-30	2009-12-01	Honeywell International Inc.	High effectiveness cooled turbine blade
US7967563B1 (en) *	2007-11-19	2011-06-28	Florida Turbine Technologies, Inc.	Turbine blade with tip section cooling channel
NZ614255A (en) *	2009-03-19	2015-03-27	Los Angeles Biomed Res Inst	Vaccine compositions and methods for treatment of mucormycosis and other fungal diseases
US8562286B2 (en) *	2010-04-06	2013-10-22	United Technologies Corporation	Dead ended bulbed rib geometry for a gas turbine engine
GB201102719D0 (en) *	2011-02-17	2011-03-30	Rolls Royce Plc	Cooled component for the turbine of a gas turbine engine
US20120315139A1 (en) *	2011-06-10	2012-12-13	General Electric Company	Cooling flow control members for turbomachine buckets and method
US8807945B2 (en)	2011-06-22	2014-08-19	United Technologies Corporation	Cooling system for turbine airfoil including ice-cream-cone-shaped pedestals
US20140093388A1 (en) *	2012-09-28	2014-04-03	Solar Turbines Incorporated	Cooled turbine blade with leading edge flow deflection and division
US9228439B2 (en) *	2012-09-28	2016-01-05	Solar Turbines Incorporated	Cooled turbine blade with leading edge flow redirection and diffusion
US9670784B2 (en)	2013-10-23	2017-06-06	General Electric Company	Turbine bucket base having serpentine cooling passage with leading edge cooling
US9638041B2 (en)	2013-10-23	2017-05-02	General Electric Company	Turbine bucket having non-axisymmetric base contour
US9528379B2 (en)	2013-10-23	2016-12-27	General Electric Company	Turbine bucket having serpentine core
US9551226B2 (en)	2013-10-23	2017-01-24	General Electric Company	Turbine bucket with endwall contour and airfoil profile
US9797258B2 (en) *	2013-10-23	2017-10-24	General Electric Company	Turbine bucket including cooling passage with turn
US10704397B2 (en)	2015-04-03	2020-07-07	Siemens Aktiengesellschaft	Turbine blade trailing edge with low flow framing channel
WO2016163980A1 (fr) *	2015-04-06	2016-10-13	Siemens Energy, Inc.	Aube de turbine avec système de refroidissement à canal en serpentin avec diviseur de flux amélioré
US10107108B2 (en)	2015-04-29	2018-10-23	General Electric Company	Rotor blade having a flared tip
DE102015112643A1 (de) *	2015-07-31	2017-02-02	Wobben Properties Gmbh	Windenergieanlagen-Rotorblatt
US10119406B2 (en) *	2016-05-12	2018-11-06	General Electric Company	Blade with stress-reducing bulbous projection at turn opening of coolant passages
WO2018143997A1 (fr) *	2017-02-03	2018-08-09	Siemens Aktiengesellschaft	Pale de turbine
EP3673152A1 (fr) *	2017-08-24	2020-07-01	Siemens Aktiengesellschaft	Profil aérodynamique de rotor de turbine et procédé correspondant pour la réduction de la perte de pression dans une cavité à l'intérieur d'une pale
US10641106B2 (en)	2017-11-13	2020-05-05	Honeywell International Inc.	Gas turbine engines with improved airfoil dust removal
US10502093B2 (en) *	2017-12-13	2019-12-10	Pratt & Whitney Canada Corp.	Turbine shroud cooling
US10718219B2 (en) *	2017-12-13	2020-07-21	Solar Turbines Incorporated	Turbine blade cooling system with tip diffuser
US10533454B2 (en)	2017-12-13	2020-01-14	Pratt & Whitney Canada Corp.	Turbine shroud cooling
US11274569B2 (en)	2017-12-13	2022-03-15	Pratt & Whitney Canada Corp.	Turbine shroud cooling
US10570773B2 (en) *	2017-12-13	2020-02-25	Pratt & Whitney Canada Corp.	Turbine shroud cooling
US10655476B2 (en) *	2017-12-14	2020-05-19	Honeywell International Inc.	Gas turbine engines with airfoils having improved dust tolerance
DE102019125779B4 (de) *	2019-09-25	2024-03-21	Man Energy Solutions Se	Schaufel einer Strömungsmaschine
US11319839B2 (en) *	2019-12-20	2022-05-03	Raytheon Technologies Corporation	Component having a dirt tolerant passage turn
CN111852574A (zh) *	2020-07-27	2020-10-30	北京全四维动力科技有限公司	涡轮叶片及包括其的燃气轮机
US11365645B2 (en)	2020-10-07	2022-06-21	Pratt & Whitney Canada Corp.	Turbine shroud cooling
KR102668653B1 (ko)	2021-10-27	2024-05-22	두산에너빌리티 주식회사	터빈용 에어포일, 이를 포함하는 터빈
CN115962015A (zh) *	2023-01-09	2023-04-14	中国航发湖南动力机械研究所	一种涡轮叶片内腔导流结构
US20260098476A1 (en) *	2024-10-09	2026-04-09	Solar Turbines Incorporated	Turbine blade with cooling features

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- 2001-12-08 DE DE50111949T patent/DE50111949D1/de not_active Expired - Lifetime
- 2001-12-13 US US10/013,666 patent/US6595750B2/en not_active Expired - Lifetime

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP1456505A1 (fr) *	2001-12-10	2004-09-15	ALSTOM Technology Ltd	Piece a sollicitation thermique
US7137784B2 (en)	2001-12-10	2006-11-21	Alstom Technology Ltd	Thermally loaded component
EP1607576A2 (fr)	2004-06-14	2005-12-21	United Technologies Corporation	Passage coudé de refroidissement d'aile et méthode de fabrication
EP1607576A3 (fr) *	2004-06-14	2009-01-14	United Technologies Corporation	Passage coudé de refroidissement d'aile et méthode de fabrication
WO2007050205A3 (fr) *	2005-09-19	2007-09-20	United Technologies Corp	Echangeur thermique compact
WO2009118245A1 (fr) *	2008-03-28	2009-10-01	Alstom Technology Ltd	Aube directrice pour turbine à gaz et turbine à gaz dotée d'une aube directrice de ce type
US8801366B2 (en)	2008-03-28	2014-08-12	Alstom Technology Ltd.	Stator blade for a gas turbine and gas turbine having same
US8985940B2 (en)	2012-03-30	2015-03-24	Solar Turbines Incorporated	Turbine cooling apparatus
WO2016148690A1 (fr) *	2015-03-17	2016-09-22	Siemens Energy, Inc.	Aube de turbine avec structure de guidage tournante à écoulement sans contrainte
US10196906B2 (en)	2015-03-17	2019-02-05	Siemens Energy, Inc.	Turbine blade with a non-constraint flow turning guide structure

Also Published As

Publication number	Publication date
DE50111949D1 (de)	2007-03-15
EP1223308A3 (fr)	2004-01-02
US6595750B2 (en)	2003-07-22
US20020176776A1 (en)	2002-11-28
EP1223308B1 (fr)	2007-01-24

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2006-06-21	RTI1	Title (correction)	Free format text: TURBOMACHINE COMPONENT
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