EP1728969A2 - Gekühlte Turbomaschinenschaufel - Google Patents
Gekühlte Turbomaschinenschaufel Download PDFInfo
- Publication number
- EP1728969A2 EP1728969A2 EP06252658A EP06252658A EP1728969A2 EP 1728969 A2 EP1728969 A2 EP 1728969A2 EP 06252658 A EP06252658 A EP 06252658A EP 06252658 A EP06252658 A EP 06252658A EP 1728969 A2 EP1728969 A2 EP 1728969A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- leg
- airfoil
- centrifugal
- intake
- passage
- 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- Withdrawn
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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
Definitions
- This invention relates to cooled airfoils of the type used in turbine engines and particularly to a cooled airfoil with reduced turning losses in an internal cooling passage of the airfoil.
- Turbine engines include one or more turbines for extracting energy from a stream of hot working medium gases.
- a typical turbine includes a rotatable hub with a set of circumferentially distributed blades projecting radially from the hub. Each blade includes an attachment for attaching the blade to the hub. Each blade also includes an airfoil that spans radially across a working medium flowpath from an airfoil root to an airfoil tip.
- a typical turbine also includes one or more arrays of stationary vanes axially spaced from the blades. Each vane includes an airfoil that spans radially across the flowpath and a hook or other feature for securing the vane to a case.
- the blades and vanes operate in a hot environment, it is common practice to provide internal coolant passages in at least the airfoils of the blades and vanes.
- coolant flows through the internal passages to protect the airfoils from the intense heat of the combustion gases.
- the coolant is usually relatively cool air that has been pressurized by a compressor powered by the turbine.
- a multi-pass passage includes at least two spanwisely extending legs that are chordwisely adjacent to each other.
- a spanwisely extending rib separates the legs from each other.
- An elbow at the radially inner or outer ends of the legs wraps around one extremity of the rib to connect the legs in series.
- a stream of coolant flows through one of the legs (the upstream leg), through the elbow and then through the other leg (the downstream leg).
- the elbow reverses the direction of coolant flow, for example from radially outwardly in the upstream leg to radially inwardly in the downstream leg.
- the coolant stream entering the downstream leg is susceptible to separation from the rib.
- the region of the leg susceptible to fluid separation extends chordwisely a considerable distance across the downstream leg and is characterized by high aerodynamic losses. These losses can imperil the durability of the airfoil by restricting coolant flow and/or by reducing the pressure of the coolant downstream of the region of separation.
- An engine designer can attempt to compensate for these effects by supplying higher pressure coolant to the passages. However such an approach may not be completely successful.
- the turbine itself is the source of energy for pressurizing the coolant, the use of higher pressure coolant degrades engine efficiency.
- an airfoil has an internal fluid passage that includes upstream and downstream legs, such as a co-centrifugal leg and a counter-centrifugal leg.
- the legs are chordwisely separated from each other by a rib but are connected in series with each other.
- the airfoil also includes a vent passage for venting fluid from the internal passage. The intake to the vent passage resides in the counter-centrifugal leg.
- FIGS. 1 and 2 show a cooled turbine blade 10 for the turbine of a gas turbine engine.
- the blade includes an attachment 12 for securing the blade to a hub, not shown.
- the hub is rotatable about an engine centerline or axis 14.
- the blade also includes a platform 16 and an airfoil 18.
- the airfoil spans radially across a working medium flowpath 20 from an airfoil root 24 to an airfoil tip 26.
- a notional chord line 28 (FIG. 2) extends from a leading edge 30 to a trailing edge 32 of the airfoil.
- Internal coolant passages such as multi-pass serpentine passage 34, convey coolant 38 through the airfoil. The coolant protects the airfoil from the intense heat of combustion gases G flowing axially through the flowpath 20.
- the passage 34 includes a spanwisely extending upstream leg 40 and a spanwisely extending downstream leg 42 chordwisely separated from the upstream leg by a spanwisely extending rib 44.
- the rib is truncated to accommodate an elbow 46 that connects the upstream and downstream legs in series flow relationship.
- the upstream leg 40 is a co-centrifugal leg because the rotation of the blade about axis 14 assists the flow of coolant from root end of the leg toward the tip end of the leg.
- the downstream leg 42 is a counter-centrifugal leg because the rotation of the blade about axis 14 resists the flow of coolant from tip end of the leg toward the root.
- the downstream leg 42 has a chordwise width W, as measured from the rib 44 to a chordwisely neighboring rib 48 that defines the opposing sidewall of the leg.
- a region 54 susceptible to fluid separation is present on the inside of the turn next to the rib 44.
- the chordwise dimension of the separation susceptible region increases with increasing lengthwise distance along the passage, and exhibits its maximum chordwise dimension at spanwise location M.
- the maximum chordwise dimension of the separation region is about 50% of the chordwise width W.
- the region 54 then diminishes in chordwise dimension with additional lengthwise distance along the passage.
- the overall spanwise dimension of the illustrated separation region 54 is about two and one half to three hydraulic diameters. This is a typical spanwise dimension for the separation region, however the spanwise dimension can vary depending on the geometry of the passage leg and the fluid properties of the coolant.
- a vent passage 56 penetrates the suction sidewall 58 of the airfoil.
- the vent passage has an intake 60 residing in the region susceptible to separation and an exit 62 on the suction wall.
- the vent passage at least partially counteracts the separation potential of region 54 by allowing some of the coolant to vent from the passage leg 42.
- the vent passage will be most effective if its inlet 60 resides immediately adjacent to rib 44 as seen best in FIG. 3.
- a vent intake chordwisely spaced from the rib by as much as about half the maximum chordwise width of the unmoderated region 54 (FIG. 4) would also be quite effective. Because the widest portion of the unmoderated separation zone (seen in FIG.
- vent intake occupies about 50% of the local passage width W, such a vent intake would be spaced from rib 44 by about 25% of the local passage width W.
- the vent intake should also be within three and one half hydraulic diameters from the inlet, more typically about two and one half to three hydraulic diameters from the inlet in order that the vent intake is within the separation region.
- the intake is at the lengthwise location M, where the chordwise dimension of the unmoderated separation susceptible region is widest.
- the vent passage may be a single passage or it may be an array of passages, one example of which is the single linear array, seen in FIG. 3.
- the above described principles for positioning the passage intakes apply equally to a single passage or to an array of passages.
- the row is centered at spanwise location M where the unmoderated separation susceptible region has its maximum chordwise dimension.
- vent passages may be installed by any suitable technique, for example laser drilling, electron beam drilling or electro-discharge machining. Since turbine blades are usually cast, the passages may also be provided for in the casting itself.
- One possible advantage to cast passages is the relative ease with which they may be precisely and repeatably positioned in a group of serially produced airfoils.
- vent passage is a film cooling hole that exhausts some of the coolant 38 to the surface of the suction wall 58 where it spreads out to form a thermally protective cooling film on the wall surface.
- a film cooling hole that vents coolant to the surface of the pressure wall 64 would also be effective, provided the pressure difference across the passage is large enough to drive the coolant through the passage.
- film cooling holes venting to both the suction and pressure sides would also be effective. Vent passages that do not also serve as film cooling holes will also suffice to moderate the region of separation.
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 |
---|---|---|---|
US11/140,851 US20070009358A1 (en) | 2005-05-31 | 2005-05-31 | Cooled airfoil with reduced internal turn losses |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1728969A2 true EP1728969A2 (de) | 2006-12-06 |
Family
ID=36675905
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06252658A Withdrawn EP1728969A2 (de) | 2005-05-31 | 2006-05-22 | Gekühlte Turbomaschinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US20070009358A1 (de) |
EP (1) | EP1728969A2 (de) |
JP (1) | JP2006336651A (de) |
AU (1) | AU2006202304A1 (de) |
RU (1) | RU2006118026A (de) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140219813A1 (en) * | 2012-09-14 | 2014-08-07 | Rafael A. Perez | Gas turbine engine serpentine cooling passage |
US9797258B2 (en) * | 2013-10-23 | 2017-10-24 | General Electric Company | Turbine bucket including cooling passage with turn |
US9726023B2 (en) * | 2015-01-26 | 2017-08-08 | United Technologies Corporation | Airfoil support and cooling scheme |
Family Cites Families (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3628885A (en) * | 1969-10-01 | 1971-12-21 | Gen Electric | Fluid-cooled airfoil |
US4162136A (en) * | 1974-04-05 | 1979-07-24 | Rolls-Royce Limited | Cooled blade for a gas turbine engine |
US4353679A (en) * | 1976-07-29 | 1982-10-12 | General Electric Company | Fluid-cooled element |
FR2468727A1 (fr) * | 1979-10-26 | 1981-05-08 | Snecma | Perfectionnement aux aubes de turbine refroidies |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
JPS62228603A (ja) * | 1986-03-31 | 1987-10-07 | Toshiba Corp | ガスタ−ビンの翼 |
US4753575A (en) * | 1987-08-06 | 1988-06-28 | United Technologies Corporation | Airfoil with nested cooling channels |
US4767268A (en) * | 1987-08-06 | 1988-08-30 | United Technologies Corporation | Triple pass cooled airfoil |
US4930980A (en) * | 1989-02-15 | 1990-06-05 | Westinghouse Electric Corp. | Cooled turbine vane |
JP3666602B2 (ja) * | 1992-11-24 | 2005-06-29 | ユナイテッド・テクノロジーズ・コーポレイション | 冷却可能なエアフォイル構造 |
US5403159A (en) * | 1992-11-30 | 1995-04-04 | United Technoligies Corporation | Coolable airfoil structure |
EP0730704B1 (de) * | 1993-11-24 | 1997-07-09 | United Technologies Corporation | Gekühlte turbinenschaufel |
US5387085A (en) * | 1994-01-07 | 1995-02-07 | General Electric Company | Turbine blade composite cooling circuit |
US5498126A (en) * | 1994-04-28 | 1996-03-12 | United Technologies Corporation | Airfoil with dual source cooling |
US5538393A (en) * | 1995-01-31 | 1996-07-23 | United Technologies Corporation | Turbine shroud segment with serpentine cooling channels having a bend passage |
US5669759A (en) * | 1995-02-03 | 1997-09-23 | United Technologies Corporation | Turbine airfoil with enhanced cooling |
US5645397A (en) * | 1995-10-10 | 1997-07-08 | United Technologies Corporation | Turbine vane assembly with multiple passage cooled vanes |
JP3411775B2 (ja) * | 1997-03-10 | 2003-06-03 | 三菱重工業株式会社 | ガスタービン動翼 |
US5827043A (en) * | 1997-06-27 | 1998-10-27 | United Technologies Corporation | Coolable airfoil |
US5902093A (en) * | 1997-08-22 | 1999-05-11 | General Electric Company | Crack arresting rotor blade |
US6004100A (en) * | 1997-11-13 | 1999-12-21 | United Technologies Corporation | Trailing edge cooling apparatus for a gas turbine airfoil |
US6474947B1 (en) * | 1998-03-13 | 2002-11-05 | Mitsubishi Heavy Industries, Ltd. | Film cooling hole construction in gas turbine moving-vanes |
DE19921644B4 (de) * | 1999-05-10 | 2012-01-05 | Alstom | Kühlbare Schaufel für eine Gasturbine |
US6241467B1 (en) * | 1999-08-02 | 2001-06-05 | United Technologies Corporation | Stator vane for a rotary machine |
US6595748B2 (en) * | 2001-08-02 | 2003-07-22 | General Electric Company | Trichannel airfoil leading edge cooling |
-
2005
- 2005-05-31 US US11/140,851 patent/US20070009358A1/en not_active Abandoned
-
2006
- 2006-05-22 EP EP06252658A patent/EP1728969A2/de not_active Withdrawn
- 2006-05-25 RU RU2006118026/06A patent/RU2006118026A/ru not_active Application Discontinuation
- 2006-05-30 AU AU2006202304A patent/AU2006202304A1/en not_active Abandoned
- 2006-05-31 JP JP2006151846A patent/JP2006336651A/ja active Pending
Also Published As
Publication number | Publication date |
---|---|
US20070009358A1 (en) | 2007-01-11 |
JP2006336651A (ja) | 2006-12-14 |
AU2006202304A1 (en) | 2006-12-14 |
RU2006118026A (ru) | 2007-12-10 |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
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AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
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AX | Request for extension of the european patent |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN |
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18W | Application withdrawn |
Effective date: 20080806 |