EP1870561B1 - Kühlung der Leitkante einer Gasturbinenkomponente mittels gestaffelt angeordneten Turbulatoren - Google Patents
Kühlung der Leitkante einer Gasturbinenkomponente mittels gestaffelt angeordneten Turbulatoren Download PDFInfo
- Publication number
- EP1870561B1 EP1870561B1 EP07252545.4A EP07252545A EP1870561B1 EP 1870561 B1 EP1870561 B1 EP 1870561B1 EP 07252545 A EP07252545 A EP 07252545A EP 1870561 B1 EP1870561 B1 EP 1870561B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- leading edge
- trip strips
- trip
- turbine engine
- engine component
- 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.)
- Revoked
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
-
- 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
-
- 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
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading 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
- F05D2240/303—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 leading 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
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Definitions
- the present invention relates to enhanced cooling of the leading edge of airfoil portions of turbine engine components using trip strips that are preferably staggered and that are wrapped around the nose of the leading edge cavity.
- FIG. 1 where there is shown an airfoil portion 10 of a turbine engine component 12. As can be seen from the figure, a radial flow leading edge cavity 14 is used to effect cooling of the leading edge region.
- FIG. 1 Another exemplary prior art cooling arrangement is shown in US 6,068,445 .
- the present invention provides a turbine engine component as set forth in claim 1.
- FIG. 2 illustrates the leading edge 30 of an airfoil portion 32 of a turbine engine component.
- the leading edge 30 has a leading edge cavity 34 in which a cooling fluid, such as engine bleed air, flows in a radial direction.
- the leading edge 30 also has a nose portion 36 and an external stagnation region 38.
- trip strips are desirable to provide adequate cooling of the leading edge, especially at the nose portion 36 of the airfoil portion 32 adjacent to the external stagnation region 38.
- the trip strip arrangement which will be discussed hereinafter provides high heat transfer to the leading edge 30 of the airfoil portion 32.
- a plurality of trip strips 40 are positioned on the pressure side 42 of the airfoil portion 32, while, as shown in FIGS. 2 , 3, and 6 , a plurality of trip strips 44 are placed on the suction side 46 of the airfoil portion 32.
- the trip strips 40 on the pressure side 42 are wrapped around the leading edge nose portion 36.
- the curvature of the leading edge nose portion 36 causes the trip strips 40 to be oriented more or less normal to the direction of flow 48 (see FIG. 6 ).
- the flow is tripped and generates a large vortex 49 at the leading edge (see FIG. 7 ). This large vortex generates very high heat transfer coefficients at the leading edge nose 36.
- the trip strips 40 and the trip strips 44 are preferably staggered approximately one half pitch apart between the suction side 46 and the pressure side 42 of the airfoil portion 32. As shown in FIGS. 2 and 7 , there is also a gap 47 between adjacent ones of the trip strips 40 and the trip strips 44. Each gap 47 is located along a parting line 70 of the airfoil portion 32.
- the orientation of the trip strips 40 and 44 in the cavity 34 also increases heat transfer at the leading edge 30 of the airfoil portion 32.
- the trip strips 40 and 44 may be oriented at an angle ⁇ of approximately 45 degrees relative to the flow direction 48.
- the leading edges 54 and 56 of the trip strips 40 and 44 are positioned in the region of highest heat load, in this case the leading edge nose 36.
- This trip strip orientation permits the creation of a turbulent vortex 49 in the cavity 34.
- the cooling fluid initially hits the leading edges 54 and 56 of the trip strip and separates from the airfoil surface. The flow then re-attaches downstream of the trip strip leading edges 54 and 56 and moves toward the divider rib 60 between the leading edge cavity 34 and the adjacent cavity 62.
- trip strip configuration allows for cooling flow to impinge on the leading edge nose 36, further enhancing heat transfer.
- the leading edge of the trip strips 40 and 44 is located near the nose 36 of the leading edge cavity 34.
- trip strips 40 although skewed at an angle ⁇ with respect to the direction of flow 48 along the pressure-side wall 42, become normal to the direction of flow 48 as they wrap around the nose 36 of the leading edge cavity 34, increasing the turbulent vortex 49 generated by the trip strips 40 and 44, and subsequently increasing the heat transfer coefficient.
- the staggered and 45 degree angled trip strips generate a vortex that impinges flow onto the nose 36 of the leading edge cavity.
- the trip strip configuration of the present invention maintains a P/E ratio between 3 and 25 where P is the radial pitch in between trip strips and E is trip strip height. Further, the trip strip configuration described herein maintains an E/H ratio of between 0.15 and 1.50 where E is trip strip height and H is the height of the cavity 34.
- Airflow testing has shown that the heat transfer coefficients at the leading edge of the airfoil adjacent to the external stagnation region when using the staggered trip strips of the present invention are enhanced by approximately two times, greatly increasing airfoil oxidation and thermo-mechanical fatigue cracking life.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (8)
- Turbinenmotorkomponente, umfassend:einen Schaufelblattabschnitt (32) mit einer Vorderkante (30), einer Ansaugseite (46), einer Druckseite (42) und einer Hinterkante;einen Radialströmungsvorderkantenhohlraum (34), durch den ein Kühlfluid strömt, um die Vorderkante zu kühlen, und eine Teilungsrippe (60) zwischen dem Vorderkantenhohlraum (34) und einem benachbarten Hohlraum (62); undein Mittel zum Erzeugen eines Wirbels (49) in dem Vorderkantenhohlraum (34), der auf einen Nasenabschnitt (36) des Vorderkantenhohlraums (34) trifft;wobei das Wirbelerzeugungsmittel eine Vielzahl erster Turbulatoren (40), die um den Nasenabschnitt (36) des Vorderkantenhohlraums (34) gewickelt ist, und eine Vielzahl zweiter Turbulatoren (44) umfasst, wobei die ersten Turbulatoren (40) an der Druckseite (42) des Schaufelblattabschnitts (32) angebracht sind und die zweiten Turbulatoren (44) an der Ansaugseite (46) des Schaufelblattabschnitts (32) angebracht sind, und wobei die ersten Turbulatoren (40) mit einem Winkel α in Bezug auf die Strömungsrichtung (48) des Kühlfluids an der Druckseite (42) des Schaufelblattabschnitts (32) abgeschrägt sind und lotrecht zur Strömungsrichtung (48) werden, während sie sich um den Nasenabschnitt (36) des Vorderkantenhohlraums (34) wickeln; wobeieine Vielzahl von Spalten (47) zwischen benachbarten der ersten Turbulatoren (40; 44) und zweiten Turbulatoren (44; 40) vorliegt;dadurch gekennzeichnet, dass die Vielzahl von Spalten (47) an einer Trennlinie (70) des Schaufelblattabschnitts (32) angeordnet ist.
- Turbinenmotorkomponente nach Anspruch 1, wobei die ersten Turbulatoren (40; 44) und zweiten Turbulatoren (44; 40) gestaffelt sind.
- Turbinenmotorkomponente nach Anspruch 1 oder 2, wobei die ersten Turbulatoren (40; 44) und zweiten Turbulatoren (44; 40) entlang einer Strömungsrichtung (48) des Kühlfluids angeordnet sind.
- Turbinenmotorkomponente nach Anspruch 3, wobei die ersten Turbulatoren (40; 44) jeweils in einem Winkel von 45 Grad relativ zur Strömungsrichtung des Kühlfluids ausgerichtet sind.
- Turbinenmotorkomponente nach Anspruch 3, wobei jeder der ersten Turbulatoren (40; 44) eine Vorderkante aufweist und die Vorderkante eines jeden Turbulators in einem Bereich mit der höchsten Wärmelast angeordnet ist.
- Turbinenmotorkomponente nach einem der Ansprüche 3 bis 5, wobei die Turbulatoren (40; 44) ein P/E-Verhältnis im Bereich von 3 bis 25 aufweisen, wobei P das radiale Abstandsmaß zwischen den Turbulatoren und E die Turbulatorhöhe ist.
- Turbinenmotorkomponente nach einem der Ansprüche 3 bis 6, wobei die Turbulatoren (40; 44) ein E/H-Verhältnis im Bereich von 0,15 bis 1,50 aufweisen, wobei E die Turbulatorhöhe ist und H die Höhe des Hohlraums ist.
- Turbinenmotorkomponente nach einem der Ansprüche 3 bis 6, wobei die ersten Turbulatoren (40; 44) und zweiten Turbulatoren (44; 40) um ein halbes Abstandsmaß zueinander gestaffelt sind.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/473,893 US20070297916A1 (en) | 2006-06-22 | 2006-06-22 | Leading edge cooling using wrapped staggered-chevron trip strips |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1870561A2 EP1870561A2 (de) | 2007-12-26 |
EP1870561A3 EP1870561A3 (de) | 2010-12-22 |
EP1870561B1 true EP1870561B1 (de) | 2017-04-05 |
Family
ID=38349575
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07252545.4A Revoked EP1870561B1 (de) | 2006-06-22 | 2007-06-22 | Kühlung der Leitkante einer Gasturbinenkomponente mittels gestaffelt angeordneten Turbulatoren |
Country Status (3)
Country | Link |
---|---|
US (1) | US20070297916A1 (de) |
EP (1) | EP1870561B1 (de) |
JP (1) | JP2008002464A (de) |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8690538B2 (en) * | 2006-06-22 | 2014-04-08 | United Technologies Corporation | Leading edge cooling using chevron trip strips |
EP1921269A1 (de) * | 2006-11-09 | 2008-05-14 | Siemens Aktiengesellschaft | Turbinenschaufel |
US8376706B2 (en) * | 2007-09-28 | 2013-02-19 | General Electric Company | Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method |
US8348613B2 (en) * | 2009-03-30 | 2013-01-08 | United Technologies Corporation | Airflow influencing airfoil feature array |
US8821111B2 (en) * | 2010-12-14 | 2014-09-02 | Siemens Energy, Inc. | Gas turbine vane with cooling channel end turn structure |
US8757961B1 (en) * | 2011-05-21 | 2014-06-24 | Florida Turbine Technologies, Inc. | Industrial turbine stator vane |
US9995148B2 (en) | 2012-10-04 | 2018-06-12 | General Electric Company | Method and apparatus for cooling gas turbine and rotor blades |
US9850762B2 (en) | 2013-03-13 | 2017-12-26 | General Electric Company | Dust mitigation for turbine blade tip turns |
EP2971544B1 (de) | 2013-03-14 | 2019-08-21 | United Technologies Corporation | Kühlung einer gasturbinenmotorkomponente mit verschachtelten, gegenüberliegenden nockenstreifen |
US10626729B2 (en) | 2013-03-14 | 2020-04-21 | United Technologies Corporation | Obtuse angle chevron trip strip |
WO2015026430A1 (en) | 2013-08-20 | 2015-02-26 | United Technologies Corporation | Ducting platform cover plate |
WO2015065717A1 (en) * | 2013-10-29 | 2015-05-07 | United Technologies Corporation | Pedestals with heat transfer augmenter |
EP3084182B8 (de) | 2013-12-20 | 2021-04-07 | Raytheon Technologies Corporation | Kühlhohlraum für gasturbinenmotorkomponente wirbelstimulierender funktion |
US10690055B2 (en) | 2014-05-29 | 2020-06-23 | General Electric Company | Engine components with impingement cooling features |
US10563514B2 (en) | 2014-05-29 | 2020-02-18 | General Electric Company | Fastback turbulator |
US9957816B2 (en) | 2014-05-29 | 2018-05-01 | General Electric Company | Angled impingement insert |
US10364684B2 (en) | 2014-05-29 | 2019-07-30 | General Electric Company | Fastback vorticor pin |
US10422235B2 (en) | 2014-05-29 | 2019-09-24 | General Electric Company | Angled impingement inserts with cooling features |
US10119404B2 (en) * | 2014-10-15 | 2018-11-06 | Honeywell International Inc. | Gas turbine engines with improved leading edge airfoil cooling |
US10280785B2 (en) | 2014-10-31 | 2019-05-07 | General Electric Company | Shroud assembly for a turbine engine |
US10233775B2 (en) | 2014-10-31 | 2019-03-19 | General Electric Company | Engine component for a gas turbine engine |
US10406596B2 (en) | 2015-05-01 | 2019-09-10 | United Technologies Corporation | Core arrangement for turbine engine component |
US10577947B2 (en) | 2015-12-07 | 2020-03-03 | United Technologies Corporation | Baffle insert for a gas turbine engine component |
US10337334B2 (en) | 2015-12-07 | 2019-07-02 | United Technologies Corporation | Gas turbine engine component with a baffle insert |
US10422233B2 (en) | 2015-12-07 | 2019-09-24 | United Technologies Corporation | Baffle insert for a gas turbine engine component and component with baffle insert |
US10280841B2 (en) | 2015-12-07 | 2019-05-07 | United Technologies Corporation | Baffle insert for a gas turbine engine component and method of cooling |
US10352177B2 (en) | 2016-02-16 | 2019-07-16 | General Electric Company | Airfoil having impingement openings |
US10590778B2 (en) | 2017-08-03 | 2020-03-17 | General Electric Company | Engine component with non-uniform chevron pins |
US10577944B2 (en) | 2017-08-03 | 2020-03-03 | General Electric Company | Engine component with hollow turbulators |
US11788416B2 (en) | 2019-01-30 | 2023-10-17 | Rtx Corporation | Gas turbine engine components having interlaced trip strip arrays |
CN115182787B (zh) * | 2022-04-27 | 2024-09-10 | 上海交通大学 | 改善前缘旋流冷却能力的涡轮叶片及发动机 |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4775296A (en) | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US5052889A (en) | 1990-05-17 | 1991-10-01 | Pratt & Whintey Canada | Offset ribs for heat transfer surface |
US5232343A (en) | 1984-05-24 | 1993-08-03 | General Electric Company | Turbine blade |
WO1995028243A1 (en) | 1994-04-19 | 1995-10-26 | United Technologies Corporation | Cooled gas turbine blade |
US5681144A (en) | 1991-12-17 | 1997-10-28 | General Electric Company | Turbine blade having offset turbulators |
US5700132A (en) | 1991-12-17 | 1997-12-23 | General Electric Company | Turbine blade having opposing wall turbulators |
EP0907005A1 (de) | 1997-04-02 | 1999-04-07 | Mitsubishi Heavy Industries, Ltd. | Turbulator für die kühlung von gasturbinenschaufeln |
US6068445A (en) | 1997-07-14 | 2000-05-30 | Abb Research Ltd. | Cooling system for the leading-edge region of a hollow gas-turbine blade |
US6406260B1 (en) | 1999-10-22 | 2002-06-18 | Pratt & Whitney Canada Corp. | Heat transfer promotion structure for internally convectively cooled airfoils |
EP1469164A2 (de) | 2003-04-15 | 2004-10-20 | General Electric Company | Gekühlte Turbinenleitschaufeln |
EP1473439A2 (de) | 2003-04-29 | 2004-11-03 | General Electric Company | Gekühlte Turbinenschaufel mit unterbrochenen Rillen |
EP1503038A1 (de) | 2003-08-01 | 2005-02-02 | Snecma Moteurs | Kühlkreislauf für eine Turbinenschaufel |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4257737A (en) * | 1978-07-10 | 1981-03-24 | United Technologies Corporation | Cooled rotor blade |
US4514144A (en) * | 1983-06-20 | 1985-04-30 | General Electric Company | Angled turbulence promoter |
GB2159585B (en) * | 1984-05-24 | 1989-02-08 | Gen Electric | Turbine blade |
JPS62271902A (ja) * | 1986-01-20 | 1987-11-26 | Hitachi Ltd | ガスタ−ビン冷却翼 |
US5246340A (en) * | 1991-11-19 | 1993-09-21 | Allied-Signal Inc. | Internally cooled airfoil |
US5695321A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
US5472316A (en) * | 1994-09-19 | 1995-12-05 | General Electric Company | Enhanced cooling apparatus for gas turbine engine airfoils |
JPH11173105A (ja) * | 1997-12-08 | 1999-06-29 | Mitsubishi Heavy Ind Ltd | ガスタービン動翼 |
JPH11241602A (ja) * | 1998-02-26 | 1999-09-07 | Toshiba Corp | ガスタービン翼 |
US8690538B2 (en) * | 2006-06-22 | 2014-04-08 | United Technologies Corporation | Leading edge cooling using chevron trip strips |
-
2006
- 2006-06-22 US US11/473,893 patent/US20070297916A1/en not_active Abandoned
-
2007
- 2007-06-19 JP JP2007160904A patent/JP2008002464A/ja active Pending
- 2007-06-22 EP EP07252545.4A patent/EP1870561B1/de not_active Revoked
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4775296A (en) | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US5232343A (en) | 1984-05-24 | 1993-08-03 | General Electric Company | Turbine blade |
US5052889A (en) | 1990-05-17 | 1991-10-01 | Pratt & Whintey Canada | Offset ribs for heat transfer surface |
US5681144A (en) | 1991-12-17 | 1997-10-28 | General Electric Company | Turbine blade having offset turbulators |
US5700132A (en) | 1991-12-17 | 1997-12-23 | General Electric Company | Turbine blade having opposing wall turbulators |
WO1995028243A1 (en) | 1994-04-19 | 1995-10-26 | United Technologies Corporation | Cooled gas turbine blade |
EP0907005A1 (de) | 1997-04-02 | 1999-04-07 | Mitsubishi Heavy Industries, Ltd. | Turbulator für die kühlung von gasturbinenschaufeln |
US6068445A (en) | 1997-07-14 | 2000-05-30 | Abb Research Ltd. | Cooling system for the leading-edge region of a hollow gas-turbine blade |
US6406260B1 (en) | 1999-10-22 | 2002-06-18 | Pratt & Whitney Canada Corp. | Heat transfer promotion structure for internally convectively cooled airfoils |
EP1469164A2 (de) | 2003-04-15 | 2004-10-20 | General Electric Company | Gekühlte Turbinenleitschaufeln |
EP1473439A2 (de) | 2003-04-29 | 2004-11-03 | General Electric Company | Gekühlte Turbinenschaufel mit unterbrochenen Rillen |
EP1503038A1 (de) | 2003-08-01 | 2005-02-02 | Snecma Moteurs | Kühlkreislauf für eine Turbinenschaufel |
Also Published As
Publication number | Publication date |
---|---|
US20070297916A1 (en) | 2007-12-27 |
JP2008002464A (ja) | 2008-01-10 |
EP1870561A2 (de) | 2007-12-26 |
EP1870561A3 (de) | 2010-12-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1870561B1 (de) | Kühlung der Leitkante einer Gasturbinenkomponente mittels gestaffelt angeordneten Turbulatoren | |
US8690538B2 (en) | Leading edge cooling using chevron trip strips | |
US7637720B1 (en) | Turbulator for a turbine airfoil cooling passage | |
US8066484B1 (en) | Film cooling hole for a turbine airfoil | |
US7311498B2 (en) | Microcircuit cooling for blades | |
EP1561902B1 (de) | Turbinenschaufel mit Turbulatoren | |
KR101434926B1 (ko) | 터빈 블레이드, 및 엔진 부품 | |
US5797726A (en) | Turbulator configuration for cooling passages or rotor blade in a gas turbine engine | |
US7097424B2 (en) | Micro-circuit platform | |
EP2825748B1 (de) | Kühlkanal für ein gasturbinentriebwerk und gasturbinentriebwerk | |
JP4063937B2 (ja) | ガスタービンエンジン内の翼の冷却通路の乱流促進構造 | |
US8066485B1 (en) | Turbine blade with tip section cooling | |
EP1961917B1 (de) | Lokal eingerückte Hinterkanten-Wärmetransferanordnungen | |
US8070441B1 (en) | Turbine airfoil with trailing edge cooling channels | |
US8297926B2 (en) | Turbine blade | |
US6183197B1 (en) | Airfoil with reduced heat load | |
JP4929097B2 (ja) | ガスタービン翼 | |
US8777569B1 (en) | Turbine vane with impingement cooling insert | |
US20090304499A1 (en) | Counter-Vortex film cooling hole design | |
EP2876258B1 (de) | Gasturbinenschaufel | |
US8061989B1 (en) | Turbine blade with near wall cooling | |
US7762775B1 (en) | Turbine airfoil with cooled thin trailing edge | |
US8491263B1 (en) | Turbine blade with cooling and sealing | |
EP1561903B1 (de) | Geschneiderte Wirbelbildung für Turbinenschaufeln | |
EP2634370B1 (de) | Turbinenschaufel mit einem Kernhohlraum mit einer konturierten Drehung |
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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 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 MT NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK RS |
|
AKY | No designation fees paid | ||
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R108 |
|
17P | Request for examination filed |
Effective date: 20110621 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): DE GB |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R108 Effective date: 20110831 |
|
17Q | First examination report despatched |
Effective date: 20120223 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: UNITED TECHNOLOGIES CORPORATION |
|
INTG | Intention to grant announced |
Effective date: 20161014 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE GB |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602007050458 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R082 Ref document number: 602007050458 Country of ref document: DE Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R026 Ref document number: 602007050458 Country of ref document: DE |
|
PLBI | Opposition filed |
Free format text: ORIGINAL CODE: 0009260 |
|
PLAX | Notice of opposition and request to file observation + time limit sent |
Free format text: ORIGINAL CODE: EPIDOSNOBS2 |
|
26 | Opposition filed |
Opponent name: SAFRAN AIRCRAFT ENGINES Effective date: 20180102 |
|
PLAF | Information modified related to communication of a notice of opposition and request to file observations + time limit |
Free format text: ORIGINAL CODE: EPIDOSCOBS2 |
|
PLBB | Reply of patent proprietor to notice(s) of opposition received |
Free format text: ORIGINAL CODE: EPIDOSNOBS3 |
|
RDAF | Communication despatched that patent is revoked |
Free format text: ORIGINAL CODE: EPIDOSNREV1 |
|
APAH | Appeal reference modified |
Free format text: ORIGINAL CODE: EPIDOSCREFNO |
|
APBM | Appeal reference recorded |
Free format text: ORIGINAL CODE: EPIDOSNREFNO |
|
APBP | Date of receipt of notice of appeal recorded |
Free format text: ORIGINAL CODE: EPIDOSNNOA2O |
|
APBQ | Date of receipt of statement of grounds of appeal recorded |
Free format text: ORIGINAL CODE: EPIDOSNNOA3O |
|
RAP2 | Party data changed (patent owner data changed or rights of a patent transferred) |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20220518 Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 602007050458 Country of ref document: DE Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US |
|
PLAB | Opposition data, opponent's data or that of the opponent's representative modified |
Free format text: ORIGINAL CODE: 0009299OPPO |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R103 Ref document number: 602007050458 Country of ref document: DE Ref country code: DE Ref legal event code: R064 Ref document number: 602007050458 Country of ref document: DE |
|
APBU | Appeal procedure closed |
Free format text: ORIGINAL CODE: EPIDOSNNOA9O |
|
R26 | Opposition filed (corrected) |
Opponent name: SAFRAN AIRCRAFT ENGINES Effective date: 20180102 |
|
RDAG | Patent revoked |
Free format text: ORIGINAL CODE: 0009271 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: PATENT REVOKED |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230519 |
|
27W | Patent revoked |
Effective date: 20230606 |
|
GBPR | Gb: patent revoked under art. 102 of the ep convention designating the uk as contracting state |
Effective date: 20230606 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230523 Year of fee payment: 17 |