EP2565382A2 - Profil d'aube avec agencement de broches de refroidissement - Google Patents
Profil d'aube avec agencement de broches de refroidissement Download PDFInfo
- Publication number
- EP2565382A2 EP2565382A2 EP12180753A EP12180753A EP2565382A2 EP 2565382 A2 EP2565382 A2 EP 2565382A2 EP 12180753 A EP12180753 A EP 12180753A EP 12180753 A EP12180753 A EP 12180753A EP 2565382 A2 EP2565382 A2 EP 2565382A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- pin
- airfoil
- cooling
- fins
- flow
- 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- Withdrawn
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
- F01D5/18—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
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
Definitions
- the present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a flow guiding pin-fin array for use in gas turbine airfoils and the like.
- a gas turbine includes a number of stages with buckets extending outwardly from a supporting rotor disk.
- Each bucket includes an airfoil over which combustion gases flow.
- the airflow must be cooled to withstand the high temperatures produced by the combustion gases. Insufficient cooling may result in undue stress on the airfoil and may lead or contribute to fatigue and/or damage.
- the airfoil thus is generally hollow with one or more internal cooling flow channels.
- the internal cooling flow channels may be provided with a cooling air bleed from the compressor or elsewhere. Convective heat transfer may be enhanced between the cooling flow and the internal metal surfaces of the airfoil by the use of pin-fin arrays, turbulators, and the like.
- the pin-fin arrays or the turbulators create a disruption in a surrounding boundary layer so as to increase heat transfer.
- An airfoil generally has a single cooling flow feed leading to a pin array and multiple outlets. Such a configuration, however, typically results in a flow through the pin array that is at an angle relative to the outlets. This angled flow may lead to a less effective heat transfer therein. Flow straighteners may be used but such add space and complexity to the pin array region.
- Such an improved cooling flow scheme may provide a pin-fin array for more effective heat transfer, better flow control, and lower manufacturing costs.
- the present invention resides in an airfoil with a cooling flow therein.
- the airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage.
- the pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.
- Fig. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
- the gas turbine engine 10 may include a compressor 12.
- the compressor 12 compresses an incoming flow of air 14.
- the compressor 12 delivers the compressed flow of air 14 to a combustor 16.
- the combustor 16 mixes the compressed flow of air 14 with a compressed flow of fuel 18 and ignites the mixture to create a flow of combustion gases 20.
- the gas turbine engine 10 may include any number of combustors 16.
- the flow of combustion gases 20 is in turn delivered to a turbine 22.
- the flow of combustion gases 20 drives the turbine 22 so as to produce mechanical work.
- the mechanical work produced in the turbine 22 drives the compressor 12 via a shaft 24 and an external load 26 such as an electrical generator and the like.
- the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
- the gas turbine engine 10 may have different configurations and may use other types of components.
- Other types of gas turbine engines also may be used herein.
- Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- Fig. 2 shows an example of a turbine bucket 28 that may be used with the turbine 22 described above.
- the turbine bucket 28 preferably may be formed as a one-piece casting of a super alloy.
- the turbine bucket 28 may include a conventional dovetail 30 attached to a conventional rotor disk.
- a blade shank 32 extends upwardly from the dovetail 30 and terminates in a platform 34 that projects outwardly from and surrounds the shank 32.
- a hollow airfoil 36 extends outwardly from the platform 34.
- the airfoil 36 has a root 38 at the junction with the platform 34 and a tip 40 at its outer end.
- the airfoil 36 has a concave pressure sidewall 42 and a convex suction sidewall 44 joined together at a leading edge 46 and a trailing edge 48.
- the airfoil 36 may include a number of trailing edge cooling holes 50 and a number of leading edge cooling holes 52.
- the airfoil 36 and the turbine bucket 28 as a whole are described herein for the purposes of example only.
- the airfoil 36 and the turbine bucket 28 may have any size or shape suitable for extracting energy from the flow of combustion gases 20. Other components and other configurations may be used herein.
- Fig. 3 shows a side cross-sectional view of the airfoil 36.
- the airfoil 36 may include a number of internal cooling pathways 54.
- the airfoil 36 may be air cooled, steam cooled, open circuit, or closed circuit.
- the leading edge cooling hole 52 may be in communication with one or more of the internal cooling pathways 54.
- the trailing edge cooling holes 50 may be in communication with one or more of the internal cooling pathways 54.
- One or more of the internal cooling pathways 54 also may include a pin array 56.
- the pin array 56 may be an array of pin-fins 58.
- the pin-fins 58 may have any desired size, shape, or configuration. In this example, the pin array 56 is positioned about the trailing edge cooling holes 50.
- Other types of heat transfer techniques may be used herein.
- Fig. 4 shows an example of the pin array 56.
- the pin-fins 58 are arranged in a uniform array 60.
- the pin-fins 58 are arranged with a generally uniform distance between each pin-fin 58.
- a cooling flow 62 may flow through the pin array 56 or other type of dump region at an angle relative to the trailing edge cooling holes 50. As described above, such an angle may compromise overall heat transfer.
- Fig. 5 shows a portion of an airfoil 100 as may be described herein.
- the airfoil 100 includes a number of internal cooling pathways 110 and a number of cooling holes 120 therethrough.
- a cooling flow 130 may flow through the internal cooling pathways 110 and exit via the cooling holes 120 so as to cool the airfoil 100.
- the cooling holes 120 may be positioned along the internal cooling pathway 110 such that the cooling flow 130 is required to make a turn in order to pass therethrough.
- Other configurations and other components may be used herein.
- the airfoil 100 also includes a pin array 140 within one or more of the internal cooling pathways 110.
- the pin array 140 may includes a number of pin-fms 150.
- the pin-fins 150 may have any desired size, shape or configuration. Any number of the pin-fins 150 may be used. Other types of flow disrupters such as turbulators and the like also may be used herein.
- the pin-fins 150 may be positioned in a non-uniform array 160.
- non-uniform array 160 we mean that the distances between the individual pin-fins 150 may vary.
- a turning opening 170 and a guiding opening 180 may be used between individual pin-fins 150.
- the turning opening 170 simply has a larger open area between the pin-fins 150 as compared to the guide opening 180.
- the turning openings 170 may be about fifteen percent (15%) to about sixty percent (60%) larger than the guiding openings 180, although other ranges may be used herein.
- the larger open area of the turning openings 170 tends to turn the cooling flow 130 in the desired direction.
- the pin-fins 150 also may have a variable downstream staggered positioning 190.
- the variable downstream staggered positioning 190 also aids in directing the cooling flow 130 as desired.
- the pin array 140 may have a number of columns: a first column 200, a second column 210, a third column 220, and a fourth column 230. Any number of columns may be used herein.
- the staggered positioning 190 thus extends across the columns.
- the cooling flow 130 thus turns into the turning opening 170 in the first column 200 and continues into the turning openings 170 of the second column 210, the third column 220, and the fourth column 230.
- the cooling flow 130 largely takes about a ninety (90) degree turn along the internal cooling pathway 110 into the cooling holes 120.
- the pin array 140 shown herein is for the purpose of example only.
- the positioning of the individual pin-fins 150 may vary according to the geometry of the airfoil 100, the internal cooling pathway 110, the cooling holes 120, the pin-fins 150, and the like. The positioning also may vary due to any number of different operational and performance parameters.
- the use of the turning openings 170 so as to turn the cooling flow 130 thus results in a more effective pin array 140 for improved heat transfer and flow control.
- the cooling flow 130 will have significant momentum component normal thereto.
- the cooling flow 130 thus is efficiently directed into the cooling holes 120 or other dump region.
- the cooling flow 130 stagnates alternatively on different pin rows so as to provide this direction.
- the pin-fins 150 are positioned so as to optimize local flow velocity. Improved heat transfer may result in lower flow requirements and enhance increased overall efficiency.
- the pin array 140 also has larger pin spacings so as to reduce manufacturing costs and complexity while still providing effective heat transfer and flow control.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/221,009 US20130052036A1 (en) | 2011-08-30 | 2011-08-30 | Pin-fin array |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2565382A2 true EP2565382A2 (fr) | 2013-03-06 |
EP2565382A3 EP2565382A3 (fr) | 2015-04-22 |
Family
ID=46679213
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20120180753 Withdrawn EP2565382A3 (fr) | 2011-08-30 | 2012-08-16 | Profil d'aube avec agencement de broches de refroidissement |
Country Status (3)
Country | Link |
---|---|
US (1) | US20130052036A1 (fr) |
EP (1) | EP2565382A3 (fr) |
CN (1) | CN102966380A (fr) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201217125D0 (en) * | 2012-09-26 | 2012-11-07 | Rolls Royce Plc | Gas turbine engine component |
US9732617B2 (en) | 2013-11-26 | 2017-08-15 | General Electric Company | Cooled airfoil trailing edge and method of cooling the airfoil trailing edge |
US9784123B2 (en) * | 2014-01-10 | 2017-10-10 | Genearl Electric Company | Turbine components with bi-material adaptive cooling pathways |
US9976425B2 (en) * | 2015-12-21 | 2018-05-22 | General Electric Company | Cooling circuit for a multi-wall blade |
CN105673089B (zh) * | 2016-03-31 | 2018-06-29 | 中国船舶重工集团公司第七�三研究所 | 一种燃气轮机涡轮无冠气膜冷却转子叶片 |
CN106014488A (zh) * | 2016-07-07 | 2016-10-12 | 周丽玲 | 一种具有纵向相交肋冷却结构的燃气透平叶片 |
US10760430B2 (en) | 2017-05-31 | 2020-09-01 | General Electric Company | Adaptively opening backup cooling pathway |
US10704399B2 (en) | 2017-05-31 | 2020-07-07 | General Electric Company | Adaptively opening cooling pathway |
US11041389B2 (en) | 2017-05-31 | 2021-06-22 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
US10927680B2 (en) | 2017-05-31 | 2021-02-23 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
EP3862537A1 (fr) * | 2020-02-10 | 2021-08-11 | General Electric Company Polska sp. z o.o. | Tuyère de turbine refoidie et segment d'aube de guidage de turbine |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3858290A (en) * | 1972-11-21 | 1975-01-07 | Avco Corp | Method of making inserts for cooled turbine blades |
FR2476207A1 (fr) * | 1980-02-19 | 1981-08-21 | Snecma | Perfectionnement aux aubes de turbines refroidies |
US5601399A (en) * | 1996-05-08 | 1997-02-11 | Alliedsignal Inc. | Internally cooled gas turbine vane |
US6254334B1 (en) * | 1999-10-05 | 2001-07-03 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
US6402470B1 (en) * | 1999-10-05 | 2002-06-11 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
US6257831B1 (en) * | 1999-10-22 | 2001-07-10 | Pratt & Whitney Canada Corp. | Cast airfoil structure with openings which do not require plugging |
DE19963349A1 (de) * | 1999-12-27 | 2001-06-28 | Abb Alstom Power Ch Ag | Schaufel für Gasturbinen mit Drosselquerschnitt an Hinterkante |
US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
US6890154B2 (en) * | 2003-08-08 | 2005-05-10 | United Technologies Corporation | Microcircuit cooling for a turbine blade |
US6981840B2 (en) * | 2003-10-24 | 2006-01-03 | General Electric Company | Converging pin cooled airfoil |
US7125225B2 (en) * | 2004-02-04 | 2006-10-24 | United Technologies Corporation | Cooled rotor blade with vibration damping device |
EP2143883A1 (fr) * | 2008-07-10 | 2010-01-13 | Siemens Aktiengesellschaft | Aube de turbine et moyau de coulée de fabrication |
-
2011
- 2011-08-30 US US13/221,009 patent/US20130052036A1/en not_active Abandoned
-
2012
- 2012-08-16 EP EP20120180753 patent/EP2565382A3/fr not_active Withdrawn
- 2012-08-30 CN CN2012103158304A patent/CN102966380A/zh active Pending
Non-Patent Citations (1)
Title |
---|
None |
Also Published As
Publication number | Publication date |
---|---|
EP2565382A3 (fr) | 2015-04-22 |
US20130052036A1 (en) | 2013-02-28 |
CN102966380A (zh) | 2013-03-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2565382A2 (fr) | Profil d'aube avec agencement de broches de refroidissement | |
EP2634369B1 (fr) | Aubes de turbine et procédé associé de fabrication | |
US8210814B2 (en) | Crossflow turbine airfoil | |
US8790083B1 (en) | Turbine airfoil with trailing edge cooling | |
US8840371B2 (en) | Methods and systems for use in regulating a temperature of components | |
EP2828483B1 (fr) | Composant de turbine a gaz comprenant une paroi refroidie | |
US8511990B2 (en) | Cooling hole exits for a turbine bucket tip shroud | |
WO2013133945A1 (fr) | Surface portant à socles à canaux de refroidissement internes améliorés | |
US8235652B2 (en) | Turbine nozzle segment | |
EP2620593A1 (fr) | Aube de turbine et procédé associé de refroidissement | |
EP2634370B1 (fr) | Aube de turbine avec cavité de noyau ayant un virage profilé | |
US8118554B1 (en) | Turbine vane with endwall cooling | |
US20170145831A1 (en) | Gas turbine engine with film holes | |
JP6438662B2 (ja) | ガスタービンエンジンのタービン動翼の冷却通路 | |
US9249675B2 (en) | Pin-fin array | |
JP5911684B2 (ja) | タービンブレードプラットフォーム冷却システム | |
JP2004028097A (ja) | タービンブレード壁の冷却装置及び製造方法 | |
EP2971545B1 (fr) | Pale refroidie à faible perte de pression | |
US9528380B2 (en) | Turbine bucket and method for cooling a turbine bucket of a gas turbine engine | |
US20180073370A1 (en) | Turbine blade cooling | |
EP2634371B1 (fr) | Aube de turbine avec nervure interne profilée | |
EP2647800B1 (fr) | Système de combustion de buse de transition | |
US20140356155A1 (en) | Nozzle Insert Rib Cap |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 5/18 20060101AFI20150317BHEP |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20151023 |