US20030021685A1 - Base material with cooling air hole - Google Patents
Base material with cooling air hole Download PDFInfo
- Publication number
- US20030021685A1 US20030021685A1 US10/183,853 US18385302A US2003021685A1 US 20030021685 A1 US20030021685 A1 US 20030021685A1 US 18385302 A US18385302 A US 18385302A US 2003021685 A1 US2003021685 A1 US 2003021685A1
- Authority
- US
- United States
- Prior art keywords
- cooling air
- air hole
- base material
- particles
- cooling
- 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
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
-
- 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
- F01D5/186—Film cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
-
- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film 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
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Definitions
- the invention relates to a base material with a cooling air hole.
- the base material is, in particular, a gas turbine part in which cooling air holes are present.
- cooling air contains dirt or dust particles.
- smaller particles can flow unhindered without further problems through the cooling air holes, which can, for example, have a diameter of between 0.5 and 1 mm, larger particles close the cooling air holes so that the cooling performance is reduced overall and there is the threat of overheating of the component.
- EP-A1-1 072 757 therefore proposes a dust-resistant, internal cooling system for turbine blading.
- the invention achieves the object of creating a base material with cooling air holes which are no longer completely closed by particles which are present in the cooling air.
- the base material is an impingement panel of a turbine blading platform.
- the particles which pollute the cooling air are located above the cooling air hole, the particles no longer close the latter, so that a certain cooling performance is advantageously always maintained by cooling air which flows past the particles and through the cooling air hole. In addition, there is a greater probability of the particles being removed from this position again by vibrations or flow fluctuations in the cooling air.
- the means can consist of the edge of the cooling air hole being uneven or having a ridge. This ridge can appear due to punching or stamping of the cooling air hole or can have already appeared during a casting process of the base material.
- the base material can be a part of a gas turbine, for example a sheet-metal part, for example therefore an impingement plate of a rotor blade platform or, generally, a cast part to be cooled.
- FIG. 1 shows a base material with a cooling air hole according to the invention in a first embodiment
- FIG. 2 represents the section along the line II-II in FIG. 1,
- FIG. 3 shows a base material with cooling air holes according to the invention in a second embodiment
- FIG. 4 shows a section through a punched cooling air hole according to the invention in a third embodiment
- FIG. 5 shows a base material with cooling air holes according to the invention in a fourth embodiment
- FIG. 6 shows a base material with cooling air holes according to the invention in a fifth embodiment
- FIG. 7 shows a base material with cooling air holes according to the invention in a sixth embodiment
- FIG. 8 shows a base material with cooling air holes according to the invention in a seventh embodiment
- FIG. 9 shows the section along the line IX-IX in FIG. 8.
- FIGS. 1 and 2 show a first embodiment of a base material 2 according to the invention with a cooling air hole 1 , FIG. 2 showing the section II-II in FIG. 1.
- a ridge 3 in the form of a star is stamped on the base material 2 .
- particles 5 which pollute cooling air 4 which flows through the cooling air holes 1 during the operation of the basic component, are located above the cooling air hole 1 , they can, advantageously, no longer close this cooling air hole 1 .
- a certain cooling performance is always maintained due to cooling air 4 which flows past the particles 5 and through the cooling air hole 1 .
- a “crown” is integrally cast into the base material 2 which is, for example, a gas turbine casting which is to be cooled.
- the “crown” has already been integrally cast into the part at the edge of the cooling air hole 1 during the manufacture of the base material 2 .
- FIG. 4 a ridge 3 appears due to punching during the manufacture of the cooling air holes 1 . This is, for example, conceivable in the case of impingement panels of gas turbines which contain the cooling air holes 1 .
- all means, which generate a ridge 3 or an uneven edge at the cooling air hole 1 are appropriate for the exemplary embodiments of FIGS. 1 to 4 , so that cooling air 4 continues to flow past the particles 5 , which are located on the cooling air hole 1 , and through the cooling air hole 1 and a certain cooling performance is maintained.
- the probability that the particles 5 will again leave their position is, furthermore, greater.
- FIGS. 5 to 8 show further exemplary embodiments, according to the invention, of a base material 2 with cooling air holes 1 .
- the cooling air hole 1 not to be circular. It can, in principle, be star-shaped, ellipsoidal or linear or consist of a circular cooling air hole 1 with lateral slots 7 .
- the circular cooling air hole 1 will have a diameter known from the prior art. In consequence, particles 5 which would normally close the cooling air hole 1 , so that it loses its function, are no longer able to close the cooling air hole 1 completely.
- the cooling air 4 continues to flow at the free ends of the cooling air hole 1 .
- Such cooling air holes 1 can, for example, be cut with a laser, a water jet or an electrode beam.
- the base material can be a part of a gas turbine, for example a sheet-metal part, therefore for example an impingement plate of a platform of a rotor blade, or a cast part to be cooled.
- Cooling air hole 2 Base material, impingement plate 3 Ridge 4 Cooling air 5 Particle 6 Stirrup 7 Slot 8 Wire mesh
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/899,031 US7052233B2 (en) | 2001-07-13 | 2004-07-27 | Base material with cooling air hole |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH12912001 | 2001-07-13 | ||
CH20011291/01 | 2001-07-13 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/899,031 Continuation US7052233B2 (en) | 2001-07-13 | 2004-07-27 | Base material with cooling air hole |
Publications (1)
Publication Number | Publication Date |
---|---|
US20030021685A1 true US20030021685A1 (en) | 2003-01-30 |
Family
ID=4565344
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/183,853 Abandoned US20030021685A1 (en) | 2001-07-13 | 2002-06-28 | Base material with cooling air hole |
US10/899,031 Expired - Fee Related US7052233B2 (en) | 2001-07-13 | 2004-07-27 | Base material with cooling air hole |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/899,031 Expired - Fee Related US7052233B2 (en) | 2001-07-13 | 2004-07-27 | Base material with cooling air hole |
Country Status (3)
Country | Link |
---|---|
US (2) | US20030021685A1 (de) |
EP (2) | EP1548237B1 (de) |
DE (2) | DE50207839D1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1635042A1 (de) * | 2004-09-13 | 2006-03-15 | Siemens Aktiengesellschaft | Prallkühlung eines Bauteils einer Strömungsmaschine und ein Verfahren zur Herstellung eines Prallkühlelementes |
US11415001B1 (en) * | 2021-03-11 | 2022-08-16 | General Electric Company | Cooling hole filter configuration |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2003098008A1 (de) * | 2002-05-22 | 2003-11-27 | Alstom Technology Ltd | Kühlbares bauteil und verfahren zur herstellung einer duchtrittsöffnung in eine m kühlbarem bauteil |
US20070048122A1 (en) * | 2005-08-30 | 2007-03-01 | United Technologies Corporation | Debris-filtering technique for gas turbine engine component air cooling system |
US7815414B2 (en) * | 2007-07-27 | 2010-10-19 | United Technologies Corporation | Airfoil mini-core plugging devices |
EP2119874A1 (de) * | 2008-05-15 | 2009-11-18 | ALSTOM Technology Ltd | Strömungsmaschine, inbesondere Turbine oder Verdichter |
EP2335855A1 (de) * | 2009-12-04 | 2011-06-22 | Siemens Aktiengesellschaft | Füllstoff beim Bohren von Durchgangslöchern von hohlen Bauteilen, ein Verfahren und Vorrichtung dafür |
US9151173B2 (en) * | 2011-12-15 | 2015-10-06 | General Electric Company | Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components |
US9650900B2 (en) * | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
EP3460216B1 (de) | 2013-02-14 | 2021-05-12 | Raytheon Technologies Corporation | Verfahren zum bestimmen ob eine komponente innerhalb einer zulässigen fertigungstoleranz liegt unter verwendung von oberflächenindikatoren |
US9709274B2 (en) | 2013-03-15 | 2017-07-18 | Rolls-Royce Plc | Auxetic structure with stress-relief features |
GB2514832A (en) * | 2013-06-07 | 2014-12-10 | Rolls Royce Deutschland & Co Kg | Cooling system |
WO2015184294A1 (en) | 2014-05-29 | 2015-12-03 | General Electric Company | Fastback turbulator |
US10364684B2 (en) | 2014-05-29 | 2019-07-30 | General Electric Company | Fastback vorticor pin |
US10233775B2 (en) | 2014-10-31 | 2019-03-19 | General Electric Company | Engine component for a gas turbine engine |
US10280785B2 (en) | 2014-10-31 | 2019-05-07 | General Electric Company | Shroud assembly for a turbine engine |
US9995151B2 (en) | 2015-08-17 | 2018-06-12 | General Electric Company | Article and manifold for thermal adjustment of a turbine component |
WO2019061088A1 (en) * | 2017-09-27 | 2019-04-04 | Changzhou Globe Co., Ltd. | PLATE FOR COOLING AN ELECTRIC TOOL |
US11078796B2 (en) | 2018-12-14 | 2021-08-03 | Raytheon Technologies Corporation | Redundant entry cooling air feed hole blockage preventer for a gas turbine engine |
US11073024B2 (en) * | 2018-12-14 | 2021-07-27 | Raytheon Technologies Corporation | Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine |
US11008872B2 (en) | 2018-12-14 | 2021-05-18 | Raytheon Technologies Corporation | Extension air feed hole blockage preventer for a gas turbine engine |
US11035248B1 (en) | 2019-11-25 | 2021-06-15 | General Electric Company | Unitary body turbine shrouds including shot peen screens integrally formed therein and turbine systems thereof |
US11959641B2 (en) | 2020-01-31 | 2024-04-16 | Rtx Corporation | Combustor shell with shaped impingement holes |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5747769A (en) * | 1995-11-13 | 1998-05-05 | General Electric Company | Method of laser forming a slot |
Family Cites Families (36)
Publication number | Priority date | Publication date | Assignee | Title |
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US3011760A (en) | 1953-10-20 | 1961-12-05 | Ernst R G Eckert | Transpiration cooled turbine blade manufactured from wires |
US3066912A (en) | 1961-03-28 | 1962-12-04 | Gen Electric | Turbine erosion protective device |
US3584972A (en) * | 1966-02-09 | 1971-06-15 | Gen Motors Corp | Laminated porous metal |
US3672787A (en) * | 1969-10-31 | 1972-06-27 | Avco Corp | Turbine blade having a cooled laminated skin |
BE755567A (fr) | 1969-12-01 | 1971-02-15 | Gen Electric | Structure d'aube fixe, pour moteur a turbines a gaz et arrangement de reglage de temperature associe |
GB1285369A (en) | 1969-12-16 | 1972-08-16 | Rolls Royce | Improvements in or relating to blades for fluid flow machines |
US3623711A (en) * | 1970-07-13 | 1971-11-30 | Avco Corp | Combustor liner cooling arrangement |
GB1508571A (en) | 1973-10-13 | 1978-04-26 | Rolls Royce | Hollow cooled blade or vane for a gas turbine engine |
US3905197A (en) | 1974-04-29 | 1975-09-16 | Carrier Corp | Power expander centrifuge |
US4040767A (en) | 1975-06-02 | 1977-08-09 | United Technologies Corporation | Coolable nozzle guide vane |
US4173458A (en) | 1977-02-28 | 1979-11-06 | Stiles Arthur G | Air cleaner |
US4221539A (en) | 1977-04-20 | 1980-09-09 | The Garrett Corporation | Laminated airfoil and method for turbomachinery |
US4192138A (en) * | 1977-08-29 | 1980-03-11 | Westinghouse Electric Corp. | Gas turbine combustor air inlet |
US4302940A (en) * | 1979-06-13 | 1981-12-01 | General Motors Corporation | Patterned porous laminated material |
US4269032A (en) | 1979-06-13 | 1981-05-26 | General Motors Corporation | Waffle pattern porous material |
US4606701A (en) | 1981-09-02 | 1986-08-19 | Westinghouse Electric Corp. | Tip structure for a cooled turbine rotor blade |
FI843605L (fi) | 1984-09-14 | 1986-03-15 | Ahlstroem Oy | Tilloppsspiral i en turbin som partikelavskiljare. |
US4705455A (en) | 1985-12-23 | 1987-11-10 | United Technologies Corporation | Convergent-divergent film coolant passage |
DE68906594T2 (de) | 1988-04-25 | 1993-08-26 | United Technologies Corp | Staubabscheider fuer eine luftgekuehlte schaufel. |
GB2227965B (en) * | 1988-10-12 | 1993-02-10 | Rolls Royce Plc | Apparatus for drilling a shaped hole in a workpiece |
US5113648A (en) * | 1990-02-28 | 1992-05-19 | Sundstrand Corporation | Combustor carbon screen |
US5183385A (en) | 1990-11-19 | 1993-02-02 | General Electric Company | Turbine blade squealer tip having air cooling holes contiguous with tip interior wall surface |
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DE4447515C2 (de) * | 1993-11-22 | 1999-02-25 | Toshiba Kawasaki Kk | Gekühlte Turbinenschaufel |
DE4422965A1 (de) | 1994-06-30 | 1996-01-04 | Mtu Muenchen Gmbh | Einrichtung zur Abscheidung von Fremdpartikeln aus der den Laufschaufeln einer Turbine zuzuführenden Kühlluft |
EP0789806B1 (de) | 1994-10-31 | 1998-07-29 | Westinghouse Electric Corporation | Gasturbinenschaufel mit gekühlter schaufelplattform |
US5771577A (en) * | 1996-05-17 | 1998-06-30 | General Electric Company | Method for making a fluid cooled article with protective coating |
JPH09324605A (ja) | 1996-06-10 | 1997-12-16 | Mitsubishi Heavy Ind Ltd | ガスタービンの翼冷却装置 |
JPH1037704A (ja) | 1996-07-19 | 1998-02-10 | Mitsubishi Heavy Ind Ltd | ガスタービンの静翼 |
US5779437A (en) | 1996-10-31 | 1998-07-14 | Pratt & Whitney Canada Inc. | Cooling passages for airfoil leading edge |
CA2262064C (en) * | 1998-02-23 | 2002-09-03 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade platform |
GB2343486B (en) | 1998-06-19 | 2000-09-20 | Rolls Royce Plc | Improvemnts in or relating to cooling systems for gas turbine engine airfoil |
DE19834376B4 (de) | 1998-07-30 | 2007-05-03 | Alstom | Verfahren, Einrichtung und Anwendung des Verfahrens zum Kühlen von Leitschaufeln in einer Gasturbinenanlage |
GB2350867B (en) * | 1999-06-09 | 2003-03-19 | Rolls Royce Plc | Gas turbine airfoil internal air system |
US6164913A (en) | 1999-07-26 | 2000-12-26 | General Electric Company | Dust resistant airfoil cooling |
-
2002
- 2002-06-25 EP EP05101306A patent/EP1548237B1/de not_active Expired - Lifetime
- 2002-06-25 DE DE50207839T patent/DE50207839D1/de not_active Expired - Lifetime
- 2002-06-25 DE DE50208671T patent/DE50208671D1/de not_active Expired - Lifetime
- 2002-06-25 EP EP02405528A patent/EP1275818B1/de not_active Expired - Lifetime
- 2002-06-28 US US10/183,853 patent/US20030021685A1/en not_active Abandoned
-
2004
- 2004-07-27 US US10/899,031 patent/US7052233B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5747769A (en) * | 1995-11-13 | 1998-05-05 | General Electric Company | Method of laser forming a slot |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1635042A1 (de) * | 2004-09-13 | 2006-03-15 | Siemens Aktiengesellschaft | Prallkühlung eines Bauteils einer Strömungsmaschine und ein Verfahren zur Herstellung eines Prallkühlelementes |
US11415001B1 (en) * | 2021-03-11 | 2022-08-16 | General Electric Company | Cooling hole filter configuration |
Also Published As
Publication number | Publication date |
---|---|
DE50207839D1 (de) | 2006-09-28 |
EP1548237B1 (de) | 2006-11-08 |
EP1275818B1 (de) | 2006-08-16 |
US7052233B2 (en) | 2006-05-30 |
EP1548237A3 (de) | 2005-08-03 |
DE50208671D1 (de) | 2006-12-21 |
EP1548237A2 (de) | 2005-06-29 |
EP1275818A1 (de) | 2003-01-15 |
US20050084371A1 (en) | 2005-04-21 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ALSTOM (SWITZERLAND) LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FRIED, REINHARD;RATHMANN, ULRICH;REEL/FRAME:013055/0152 Effective date: 20020603 |
|
AS | Assignment |
Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ALSTOM (SWITZERLAND) LTD;REEL/FRAME:014770/0783 Effective date: 20031101 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |