US3635585A - Gas-cooled turbine blade - Google Patents

Gas-cooled turbine blade Download PDF

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Publication number
US3635585A
US3635585A US887544A US3635585DA US3635585A US 3635585 A US3635585 A US 3635585A US 887544 A US887544 A US 887544A US 3635585D A US3635585D A US 3635585DA US 3635585 A US3635585 A US 3635585A
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United States
Prior art keywords
blade
pressure
point
leading
low
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.)
Expired - Lifetime
Application number
US887544A
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English (en)
Inventor
Charles Walter Metzler Jr
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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.)
Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Application granted granted Critical
Publication of US3635585A publication Critical patent/US3635585A/en
Anticipated expiration legal-status Critical
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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
    • 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • ABSTRACT A cooled turbine blade for gas turbines and the like having 52 11.s.c1 ..4116/96, 416/92, 416/97 passageways for conducting a relatively c001 fluid through the 51 1m. (:1 ..]F01d s/w blade to its tip and incorporating a Walled cavity at the p of 53 Field ofSearch ..4l6/96, 97, 92, 95 the blade
  • the Wall Ofthe cavity has a cutaway P" which permits the cooling fluid to discharge into a main gas stream 6 R E d through the turbine at the area of lowest pressure on the blade [5 l e erences l e surfaces.
  • the cooling passages terminate at openings in the extreme end or tip of the blade.
  • This has several disadvantages.
  • the pressure on the blade at its leading edge is greater than at its trailing edge.
  • the cooling fluid in the passages at the leading edge must discharge into an area of greater pressure than the passages at the trailing edge, meaning that the flow of fluid and heat transfer efficiency at the leading edge is impeded.
  • the tip clearance between the end of the blade and the stationary turbine wall must be greater than it otherwise would be; and the tolerances become more critical.
  • the pressure on the cooling fluid must be increased to the point where it can be effectively discharged into a high-pressure gas stream.
  • the foregoing drawbacks associated with prior art cooling systems are overcome by a construction wherein the blade is provided with a walled cavity at its tip.
  • the cooling passages terminate at the bottom of the cavity; while the extremity of the cavity wall is adjacent the turbine casing, and, in effect, constitutes the end of the blade.
  • a portion of the wall is cutaway on the low-pressure side of the blade adjacent its trailing edge such that the passages in the blade do not discharge into the main turbine gas stream but rather into a relatively constant pressure area within the cavity.
  • the wall of the cavity is cut away adjacent to the trailing edge of the blade on its low-pressure side, the cavity is exposed to the lowest discharge pressure possible with a minimum disturbance to the main flow through the turbine.
  • the pressure on the cooling system can be reduced and, at the same time, the flow offluid through the cooling passages from the leading edge of the blade to its trailing edge is essentially the same throughout.
  • FIG. I is a fragmentary elevational view of a turbine rotor having the blades of the invention thereon;
  • FIG. 2 is a top view taken substantially along line II-II of FIG. I, but on a larger scale, showing the walled cavity tip construction of the blades of the invention;
  • FIG. 3 is a cross-sectional development view through the curved center of a blade taken substantially along line III-III of FIG. 2;
  • FIG. 4 is a perspective view of the blade tip ofthe invention.
  • FIG. 1 there is shown, by way of example, part of a gas turbine rotor structure including a rotor shaft which is connected to a rotor disc 12 projecting radially from the shaft axis.
  • the rim 14 of the disc 12 is formed with a continuous se ries of transverse side entry" recesses 16, each of which is broadly V-shaped but having sidewalls formed with adjacent secondary transverse serrations or grooves 17.
  • the turbine blades 18, as perhaps best shown in FIGS. 2 and 4, have the usual airfoil shape with rounded leading edges 20, thin trailing edges 22 and curved profiles.
  • the blade root 24 (FIG. I is in the form of a triangular elongated block with the blade Id integral with its one side and the two other sides having adjacent transverse grooves therein, which grooves conform to and are adapted to register with the grooves I7 formed in the transverse recesses I6 of the disc rim M, thus forming the well-known fir tree base connection. Attachment is made by sliding the blade root into the disc rim recess so that the grooves and ridges of the two parts are in cooperative engagement.
  • Suitable means are provided for maintaining the roots 24 within their cooperating recesses 16.
  • suitable means, not shown, but well within the skill of the art are provided for conducting a cool ing fluid such as air up through the root portions 241 and into radial passages extending through each of the blades I8.
  • the radial passageways 26 are shown in FIGS. 2, 3 and 4 and extend all the way from the root 24 to the tip or outer radial extremity of each blade.
  • the lower sides of the blades I8 as viewed in FIG. 2 are referred to as the high-pressure sides 29 and are those sides against which hot gases under pressure are directed in order to cause the rotor to turn in the direction of arrow 30 shown in FIG. I.
  • the other side 32 of each blade also extends between the leading and trailing edges 20 and 22 and is referred to as the low-pressure side.
  • Hot gases, in passing through the blades, generally follow the path of arrows 34.
  • the point of highest pressure on the blades is at the high-pressure side 29 adjacent the leading edge 20. As the gas travels from the leading to the trailing edge of the blade, it expands and its pressure reduces. Consequently, the point of lowest pressure is at the low-pressure side 32 near the throat area B.
  • each blade I8 is provided with a walled cavity, generally indicated by the reference numeral 36 in FIGS. 24, which is formed by a wall 38 extending along the top of the high-pressure side 29 from the trailing edge 22 to the leading edge 20 and thence along approximately one-half the length of the low-pressure side 32 to point A which is just downstream of the throat B between the trailing edge 22 of one blade and the low-pressure side of the following blade.
  • the radial passageways 26 terminate at the bottom 37 of the cavity 36, as perhaps best shown in FIG. 3.
  • the gas discharges into an area within the cavity 36 of relatively constant pressure, meaning that the pressure which gases issuing from the passageways 26 at the leading edge 20 experience is approximately the same as that experienced by the gas leaving the passageways 26 adjacent the trailing edge 22.
  • the depth of the cavity 36 is adjusted to provide an area at C which is substantially greater than the combined area of the cross sections of the cooling passages 26 upstream of point A. This permits the discharge pressure for the upstream holes to approach the pressure at point A, approximately the lowest pressure on the blade surface.
  • the present invention thus provides a means for attaining a uniform flow of cooling fluid through radial passages in a turbine blade from its leading to its trailing edge, independent of operating tip clearances between the Iblade tip and the stationary turbine walls. At the same time, the cooling air enters the main stream through the turbine in more nearly the correct direction for mixing with the main gas stream, thereby reducing mixing losses.
  • a turbine blade of the type having a root portion, a tip portion, leading and trailing edge portions, a low-pressure surface extending between said leading and trailing edges. a highpressure surface continuous with said low-pressure surface and extending between said leading and trailing edges, and a plurality of passages of uniform cross-sectional area extending from said root portion to said tip portion of the blade for con ducting a cooling fluid through the blade; the improvement comprising a walled cavity at the outermost tip portion of said blade having a bottom at which said passages terminate and a cutaway portion in its wall extending between said trailing edge and a point on said low-pressure side which permits the cooling fluid to discharge into the main gas stream through the turbine at the point of substantially lowest pressure on the blade surfaces, and said wall being a continuous extension of the outer high-pressure and low-pressure surfaces.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US887544A 1969-12-23 1969-12-23 Gas-cooled turbine blade Expired - Lifetime US3635585A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US88754469A 1969-12-23 1969-12-23

Publications (1)

Publication Number Publication Date
US3635585A true US3635585A (en) 1972-01-18

Family

ID=25391380

Family Applications (1)

Application Number Title Priority Date Filing Date
US887544A Expired - Lifetime US3635585A (en) 1969-12-23 1969-12-23 Gas-cooled turbine blade

Country Status (7)

Country Link
US (1) US3635585A (de)
BE (1) BE760728A (de)
CH (1) CH533760A (de)
DE (1) DE2060123B2 (de)
FR (1) FR2074130A5 (de)
GB (1) GB1282796A (de)
NL (1) NL7017527A (de)

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876330A (en) * 1972-04-20 1975-04-08 Rolls Royce 1971 Ltd Rotor blades for fluid flow machines
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US4606701A (en) * 1981-09-02 1986-08-19 Westinghouse Electric Corp. Tip structure for a cooled turbine rotor blade
US4761116A (en) * 1987-05-11 1988-08-02 General Electric Company Turbine blade with tip vent
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
US5261789A (en) * 1992-08-25 1993-11-16 General Electric Company Tip cooled blade
US5503527A (en) * 1994-12-19 1996-04-02 General Electric Company Turbine blade having tip slot
US5564902A (en) * 1994-04-21 1996-10-15 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine rotor blade tip cooling device
US5927946A (en) * 1997-09-29 1999-07-27 General Electric Company Turbine blade having recuperative trailing edge tip cooling
US5980209A (en) * 1997-06-27 1999-11-09 General Electric Co. Turbine blade with enhanced cooling and profile optimization
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
EP1367222A2 (de) * 2002-05-31 2003-12-03 General Electric Company Methode und Einrichtung zur Verminderung der Temperatur von Schaufelblattspitzen
US20050196277A1 (en) * 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
US20070258815A1 (en) * 2006-05-02 2007-11-08 Siemens Power Generation, Inc. Turbine blade with wavy squealer tip rail
US20080044290A1 (en) * 2006-08-21 2008-02-21 General Electric Company Conformal tip baffle airfoil
US20080044291A1 (en) * 2006-08-21 2008-02-21 General Electric Company Counter tip baffle airfoil
US20080044289A1 (en) * 2006-08-21 2008-02-21 General Electric Company Tip ramp turbine blade
US20080118363A1 (en) * 2006-11-20 2008-05-22 General Electric Company Triforial tip cavity airfoil
JP2009108834A (ja) * 2007-11-01 2009-05-21 Ihi Corp スキーラ付きタービン動翼
US20090162200A1 (en) * 2007-12-19 2009-06-25 Rolls-Royce Plc Rotor blades
US7597539B1 (en) 2006-09-27 2009-10-06 Florida Turbine Technologies, Inc. Turbine blade with vortex cooled end tip rail
US20090324422A1 (en) * 2006-08-21 2009-12-31 General Electric Company Cascade tip baffle airfoil
US20100080711A1 (en) * 2006-09-20 2010-04-01 United Technologies Corporation Turbine blade with improved durability tip cap
US20100111704A1 (en) * 2008-10-30 2010-05-06 Mitsubishi Heavy Industries, Ltd. Turbine blade having squealer
US20100189569A1 (en) * 2009-01-26 2010-07-29 Rolls-Royce Plc Rotor blade
US20100221122A1 (en) * 2006-08-21 2010-09-02 General Electric Company Flared tip turbine blade
US20100303625A1 (en) * 2009-05-27 2010-12-02 Craig Miller Kuhne Recovery tip turbine blade
US8011889B1 (en) * 2007-09-07 2011-09-06 Florida Turbine Technologies, Inc. Turbine blade with trailing edge tip corner cooling
US20110255986A1 (en) * 2010-04-19 2011-10-20 Rolls-Royce Plc Blades
EP2586984A3 (de) * 2011-10-28 2014-06-11 General Electric Company Turbinenlaufschaufel und zugehörige Turbomaschine
US8967959B2 (en) 2011-10-28 2015-03-03 General Electric Company Turbine of a turbomachine
US8992179B2 (en) 2011-10-28 2015-03-31 General Electric Company Turbine of a turbomachine
CN104775854A (zh) * 2015-04-23 2015-07-15 华能国际电力股份有限公司 一种具有抑制叶顶泄漏和减小叶顶温度的动叶顶部结构
US9255480B2 (en) 2011-10-28 2016-02-09 General Electric Company Turbine of a turbomachine
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
US20170226868A1 (en) * 2016-02-09 2017-08-10 General Electric Company Gas turbine engine airfoil
US20180073372A1 (en) * 2016-09-14 2018-03-15 Rolls-Royce Plc Turbine blade cooling
US20180073370A1 (en) * 2016-09-14 2018-03-15 Rolls-Royce Plc Turbine blade cooling
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
US11118462B2 (en) * 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
US11371359B2 (en) 2020-11-26 2022-06-28 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9607578D0 (en) * 1996-04-12 1996-06-12 Rolls Royce Plc Turbine rotor blades
US7540705B2 (en) 2006-02-01 2009-06-02 Emshey Garry Horizontal multi-blade wind turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920641C (de) * 1943-07-15 1954-11-25 Maschf Augsburg Nuernberg Ag Gekuehlte Hohlschaufel, insbesondere fuer Gasturbinen
US2888243A (en) * 1956-10-22 1959-05-26 Pollock Robert Stephen Cooled turbine blade
US3057597A (en) * 1959-08-20 1962-10-09 Jr Andre J Meyer Modification and improvements to cooled blades
US3164367A (en) * 1962-11-21 1965-01-05 Gen Electric Gas turbine blade
US3533712A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920641C (de) * 1943-07-15 1954-11-25 Maschf Augsburg Nuernberg Ag Gekuehlte Hohlschaufel, insbesondere fuer Gasturbinen
US2888243A (en) * 1956-10-22 1959-05-26 Pollock Robert Stephen Cooled turbine blade
US3057597A (en) * 1959-08-20 1962-10-09 Jr Andre J Meyer Modification and improvements to cooled blades
US3164367A (en) * 1962-11-21 1965-01-05 Gen Electric Gas turbine blade
US3533712A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines

Cited By (67)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3885609A (en) * 1972-01-18 1975-05-27 Oskar Frei Cooled rotor blade for a gas turbine
US3876330A (en) * 1972-04-20 1975-04-08 Rolls Royce 1971 Ltd Rotor blades for fluid flow machines
US4606701A (en) * 1981-09-02 1986-08-19 Westinghouse Electric Corp. Tip structure for a cooled turbine rotor blade
US4761116A (en) * 1987-05-11 1988-08-02 General Electric Company Turbine blade with tip vent
US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
US5261789A (en) * 1992-08-25 1993-11-16 General Electric Company Tip cooled blade
US5564902A (en) * 1994-04-21 1996-10-15 Mitsubishi Jukogyo Kabushiki Kaisha Gas turbine rotor blade tip cooling device
US5503527A (en) * 1994-12-19 1996-04-02 General Electric Company Turbine blade having tip slot
US5980209A (en) * 1997-06-27 1999-11-09 General Electric Co. Turbine blade with enhanced cooling and profile optimization
US5927946A (en) * 1997-09-29 1999-07-27 General Electric Company Turbine blade having recuperative trailing edge tip cooling
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
EP1367222A2 (de) * 2002-05-31 2003-12-03 General Electric Company Methode und Einrichtung zur Verminderung der Temperatur von Schaufelblattspitzen
US20050196277A1 (en) * 2004-03-02 2005-09-08 General Electric Company Gas turbine bucket tip cap
GB2412144A (en) * 2004-03-02 2005-09-21 Gen Electric Gas turbine bucket tip cap
US7001151B2 (en) 2004-03-02 2006-02-21 General Electric Company Gas turbine bucket tip cap
CN100404793C (zh) * 2004-03-02 2008-07-23 通用电气公司 燃气涡轮叶片梢帽
US20070258815A1 (en) * 2006-05-02 2007-11-08 Siemens Power Generation, Inc. Turbine blade with wavy squealer tip rail
US7513743B2 (en) * 2006-05-02 2009-04-07 Siemens Energy, Inc. Turbine blade with wavy squealer tip rail
US8512003B2 (en) 2006-08-21 2013-08-20 General Electric Company Tip ramp turbine blade
US20100221122A1 (en) * 2006-08-21 2010-09-02 General Electric Company Flared tip turbine blade
US20080044289A1 (en) * 2006-08-21 2008-02-21 General Electric Company Tip ramp turbine blade
US20080044291A1 (en) * 2006-08-21 2008-02-21 General Electric Company Counter tip baffle airfoil
US8500396B2 (en) 2006-08-21 2013-08-06 General Electric Company Cascade tip baffle airfoil
US20080044290A1 (en) * 2006-08-21 2008-02-21 General Electric Company Conformal tip baffle airfoil
US8632311B2 (en) 2006-08-21 2014-01-21 General Electric Company Flared tip turbine blade
US7607893B2 (en) 2006-08-21 2009-10-27 General Electric Company Counter tip baffle airfoil
US20090324422A1 (en) * 2006-08-21 2009-12-31 General Electric Company Cascade tip baffle airfoil
US7686578B2 (en) 2006-08-21 2010-03-30 General Electric Company Conformal tip baffle airfoil
US7726944B2 (en) * 2006-09-20 2010-06-01 United Technologies Corporation Turbine blade with improved durability tip cap
US20100080711A1 (en) * 2006-09-20 2010-04-01 United Technologies Corporation Turbine blade with improved durability tip cap
US7597539B1 (en) 2006-09-27 2009-10-06 Florida Turbine Technologies, Inc. Turbine blade with vortex cooled end tip rail
US8425183B2 (en) 2006-11-20 2013-04-23 General Electric Company Triforial tip cavity airfoil
US20080118363A1 (en) * 2006-11-20 2008-05-22 General Electric Company Triforial tip cavity airfoil
US8011889B1 (en) * 2007-09-07 2011-09-06 Florida Turbine Technologies, Inc. Turbine blade with trailing edge tip corner cooling
JP2009108834A (ja) * 2007-11-01 2009-05-21 Ihi Corp スキーラ付きタービン動翼
US20090162200A1 (en) * 2007-12-19 2009-06-25 Rolls-Royce Plc Rotor blades
US8133032B2 (en) * 2007-12-19 2012-03-13 Rolls-Royce, Plc Rotor blades
CN102057134B (zh) * 2008-10-30 2015-04-22 三菱日立电力系统株式会社 具有削薄接片的涡轮动叶片
CN102057134A (zh) * 2008-10-30 2011-05-11 三菱重工业株式会社 具有削薄接片的涡轮动叶片
EP2351908A1 (de) * 2008-10-30 2011-08-03 Mitsubishi Heavy Industries, Ltd. Bewegliche turbinenschaufel mit spitzenverdünnung
US20100111704A1 (en) * 2008-10-30 2010-05-06 Mitsubishi Heavy Industries, Ltd. Turbine blade having squealer
JPWO2010050261A1 (ja) * 2008-10-30 2012-03-29 三菱重工業株式会社 チップシニングを備えたタービン動翼
JP5031103B2 (ja) * 2008-10-30 2012-09-19 三菱重工業株式会社 チップシニングを備えたタービン動翼
EP2351908A4 (de) * 2008-10-30 2013-07-10 Mitsubishi Heavy Ind Ltd Bewegliche turbinenschaufel mit spitzenverdünnung
US8414262B2 (en) 2008-10-30 2013-04-09 Mitsubishi Heavy Industries, Ltd. Turbine blade having squealer
WO2010050261A1 (ja) * 2008-10-30 2010-05-06 三菱重工業株式会社 チップシニングを備えたタービン動翼
US8366393B2 (en) 2009-01-26 2013-02-05 Rolls-Royce Plc Rotor blade
US20100189569A1 (en) * 2009-01-26 2010-07-29 Rolls-Royce Plc Rotor blade
US20100303625A1 (en) * 2009-05-27 2010-12-02 Craig Miller Kuhne Recovery tip turbine blade
US8186965B2 (en) 2009-05-27 2012-05-29 General Electric Company Recovery tip turbine blade
US20110255986A1 (en) * 2010-04-19 2011-10-20 Rolls-Royce Plc Blades
US8845280B2 (en) * 2010-04-19 2014-09-30 Rolls-Royce Plc Blades
US9255480B2 (en) 2011-10-28 2016-02-09 General Electric Company Turbine of a turbomachine
US8992179B2 (en) 2011-10-28 2015-03-31 General Electric Company Turbine of a turbomachine
US8967959B2 (en) 2011-10-28 2015-03-03 General Electric Company Turbine of a turbomachine
US9051843B2 (en) 2011-10-28 2015-06-09 General Electric Company Turbomachine blade including a squeeler pocket
EP2586984A3 (de) * 2011-10-28 2014-06-11 General Electric Company Turbinenlaufschaufel und zugehörige Turbomaschine
US9359902B2 (en) 2013-06-28 2016-06-07 Siemens Energy, Inc. Turbine airfoil with ambient cooling system
CN104775854A (zh) * 2015-04-23 2015-07-15 华能国际电力股份有限公司 一种具有抑制叶顶泄漏和减小叶顶温度的动叶顶部结构
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
US20170226868A1 (en) * 2016-02-09 2017-08-10 General Electric Company Gas turbine engine airfoil
US10329922B2 (en) * 2016-02-09 2019-06-25 General Electric Company Gas turbine engine airfoil
US20180073372A1 (en) * 2016-09-14 2018-03-15 Rolls-Royce Plc Turbine blade cooling
US20180073370A1 (en) * 2016-09-14 2018-03-15 Rolls-Royce Plc Turbine blade cooling
US10822960B2 (en) * 2016-09-14 2020-11-03 Rolls-Royce Plc Turbine blade cooling
US11118462B2 (en) * 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
US11371359B2 (en) 2020-11-26 2022-06-28 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine

Also Published As

Publication number Publication date
FR2074130A5 (de) 1971-10-01
DE2060123B2 (de) 1979-04-26
DE2060123A1 (de) 1971-07-01
CH533760A (de) 1973-02-15
NL7017527A (de) 1971-06-25
GB1282796A (en) 1972-07-26
BE760728A (fr) 1971-06-23

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