US3369792A - Airfoil vane - Google Patents
Airfoil vane Download PDFInfo
- Publication number
- US3369792A US3369792A US540967A US54096766A US3369792A US 3369792 A US3369792 A US 3369792A US 540967 A US540967 A US 540967A US 54096766 A US54096766 A US 54096766A US 3369792 A US3369792 A US 3369792A
- Authority
- US
- United States
- Prior art keywords
- vane
- insert
- ribs
- fluid
- 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.)
- Expired - Lifetime
Links
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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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a fluid directing element and more particularly, to airfoil vane structure employing hollow vanes with insert means for directing minimum fluid flow for adequate cooling of jet engine parts such as turbine diaphragms.
- Various nozzle vane structures have been designed to permit the circulation of cooling fluids and adequately reduce temperatures.
- some designs employ cast-in passages wherein cooling fluids are circulated in a sinuous manner through the passages within the walls of the particular component such as a turbine bucket or vane.
- the problem with such designs is that the casting procedure becomes a difficult operation wherein the passages are formed by providing the transverse walls across the vanes as a part of the casting. This results in temperature gradients that produce thermal stress concentrations which often result in cracking and inadequate life. Also, the casting operation is diflicult and expensive.
- any suitable means such as inserts, are provided to confine and guide the cooling fluid adequately to cool the desired parts of the vane exposed to the hot fluids.
- the insert means acts as a baffle or guiding structure to direct the cooling fluid in a sinuous manner and discharge it after it has performed its cooling purposes.
- the maximum amount of cooling with the minimum amount of cooling fluid is desired and various internal structures have been proposed to achieve this end.
- the main object of the present invention is to provide a fluid directing element in the shape of an airfoil vane for a turbine diaphragm wherein each vane is hollow and has insert means therein to guide cooling fluid, the insert mean-s being so formed to direct a minimum flow through passages within the vane in a highly eflicient manner.
- Another object is to provide such a structure wherein the vane may be an easily cast structure adapted to support insert means which direct cooling fluid for maximum cooling with the minimum amount of fluid by an eflicient recirculating arrangement.
- a further object is to provide such structure wherein the internal insert means of the vane is an easily produced structure that slips into place to provide eflicient circulation of cooling fluid.
- a further object is to provide such a structure wherein the insert means in the hollow vanes comprises several inserts that are shorter than the vane and are staggered and 3,369,792 Patented Feb. 20, 1968 easily held in position by the vane itself to provide a sinuous cooling flow arrangement to avoid thermal stresses.
- the invention provides a fluid directing element for turbomachinery in which the element is a hollow airfoil vane having leading and trailing edges.
- Forming part of the vane, which may be cast, are preferably two pairs of axially spaced and longitudinally extending ribs on opposite internal surfaces of the hollow airfoil.
- a pair of thin-walled generally U-shaped and longitudinally shorter insert means extend lengthwise of the vane internally thereof from one end of the vane.
- Each insert which may be of sheet metal construction but is not limited to such material, has crimped surfaces on opposite legs of the U and spans a pair of the ribs whereby the insert may be slid along said ribs longitudinally into the vane to form a longitudinal baflie with a longitudinal passage between the inserts.
- Means are provided to limit the extension of the insert into the vane so that the shorter inserts are disposed to define cross passages at opposite ends respectively of adjacent inserts.
- Blocking means is proreverse the fluid flow and means are provided at opposite ends of the vane to permit fluid entry and exit.
- inserts are preferably disposed to form cooling passages adjacent the leading and trailing edges and the blocking means may comprise caps across the vane ends. Cooling means is also provided in the trailing edge to discharge fluid adjacent and transverse to the edge.
- the inserts may have tab means at their opposite ends to limit their extension into the vane.
- FIGURE 1 is a perspective view of a typical nozzle segment of vanes as used in a turbine diaphragm
- FIGURE 2 is a cross sectional view through an individual vane of the invention.
- FIGURE 3 is a cross sectional view taken on the line 33 of FIGURE 2.
- the present structure is described for convenience as one of the vanes of a turbine diaphragm structure but it will be appreciated that the specific structure described may have application elsewhere such as struts or other engine components such as airfoil-like structure requiring similar cooling capabilities.
- FIGURE 1 there is shown a single vane segment of a turbine diaphragm structure including outer band 10 and inner band 12 having nozzle vanes 14 between the bands.
- Vane 14 is hollow, as shown, and is a fluid directing element of an airfoil shape as is well known. Any number of vanes per segment may be employed or single vanes may be used in arrangements being known.
- FIGURE 1 is merely illustrative of a typical construction. It will be appreciated that a multiplicity of the vane elements in the segments of FIGURE 1 may comprise the turbine diaphragm structure that extends completely around an annulus downstream of a combustor in a jet engine and receives the hot combustor gases.
- nozzle vane elements may be employed as other stages in a multi-stage application. They direct the hot gases onto the rotating buckets, not shown, in the usual manner. Ease of assembly and lower cost construction has indicated that the diaphragm structure may conveniently be made in segments of multiple vanes or single vanes andthe segments can be cast with the individual nozzle vanes 14 therein. A multiplicity of such segments are then joined to form a circle.
- the bands may have upstream flanges 16 and downstream flanges 18 to abut the normal adjacent engine structure in the conventional manner. Similar flanges may be provided on the inner band 12 for supporting internal sealing structure in a known manner. To reduce costs and obtain high heat transfer coefficients for adequate cooling with the minimum amount of cooling fluid, it is possible to cast the whole structure shown in FIGURE 1 and bolt individual segments or vanes together as previously noted.
- FIGURE 2 showing a cross section of an individual fluid directing element or hollow airfoil vane 14.
- the hollow vane 14 is of airfoil shape and has leading and trailing edges 20 and 22 respectively.
- the airfoil shape provides a suction or convex surface 24 and a pressure or concave surface 26.
- surface 24 is exposed to higher outside heat transfer coefficients than is surface 26 and therefore requires more internal cooling.
- leading edge 29' is generally exposed to higher temperatures and requires more cooling.
- a suitable source such as compressor bleed
- insert means which will be described. It is desired that the inserts be inexpensive and easily assembled by merely slipping into position to avoid the need for the cast-in cross ribs which are difiicult to provide.
- each of the cast vanes is provided with longitudinally extending ribs 26 that are disposed on opposite internal surfaces of the hollow airfoil and are preferably provided in pairs, as shown, directiy opposite one another as better seen in FIGURE 3. These ribs means extend from one end of the vane to the other as shown.
- thin-walled generally U-shaped insert means 30 are provided. Preferably a pair of such insert means, as shown in FIGURE 3, are provided to clamp on each rib 28 as shown.
- the inserts are longitudinally shorter than the length of the vane as seen in FIGURE 2 and are staggered as will be further explained.
- each insert extend lengthwise of the vane from one end and each insert has crimped surfaces 3-2 on opposite legs of the U. These surfaces are designed to span the ribs 28 and lock the insert in position as will be apparent. Additionally, the ribs then form a track whereby the insert may be slid along the ribs into the vane toform a longitudinal baffle, and where two inserts are used as shown in FIG- URE 3, a longitudinal passage 34 is thus formed between the inserts.
- the longitudinal ribs 28 and insert means 30 are'preferably disposed inwardly from the leading and trailing edges as shown in FIGURES 2 and 3 to form longitudinal passages 36 and 38 immediately adjacent the leading and trailing edges respectively.
- the inserts may be inserted into the vane from one end and secured in position by having tab means 44 and 46 at respectively opposite ends of the inserts to provide the sinuous passage for the cooling fluid through the vane.
- any suitable locating means such as suitably secured tabs 44 and 46 may be used to position the inserts in the staggered position shown.
- cap means 48 and 50 are used as blockers across the vane ends and are disposed opposite the cross passages, as shown, whereby the fluid flow is reversed from one passage to the next.
- an inlet means 52 and exit means 54 are provided at opposite ends of the vane. It is generally desired to cool the trailing edge of the vane and to this end suitable apertures 56 are provided whereby the cooling fluid in the passage adjacent the trailing edge may exit transversely through apertures 56 as well as outlet 54. Thus, outlet 54 and apertures 56 may be metering means to determine the required amount of fluid for cooling. After exit from outlet 54 the fluid may be used elsewhere such as for sealing or use in other appropriate structure.
- the fluid discharging through apertures 5a is preferably adjacent and transverse to the trailing edge as shown in FIGURE 3 and may be on the suction side 24- as shown or it may be directed centrally out the trailing edge depending on the cooling requirements.
- the U-shaped insert means may be spring-clips that are easily held in position as shown in FIGURE 3 and are insertable from one end such as the wide end when in a tapered vane as shown in FIGURE 2.
- a simple tack weld may be used to lock the inserts in position by their tabs directly to the caps 48 and 50 to provide a light weight highly efficient cooled vane as shown. This arrangement extracts maximum heat transfer capability out of minimum cooling fluid after which it may be used for other purposes. This results in a better engine cycle when used in a gas turbine engine since the least amount is being withdrawn from the cycle.
- a fluid directing element for turbomachinery comprising, a hollow airfoil vane having leading and trailing edges,
- said insert having crimped surfaces on opposite legs of the U and spanning said ribs whereby said insert may be slid along said ribs into said vane to form a longitudinal baffle
- a fluid directing element for turbomachinery comprising, a hollow airfoil vane having leading and trailing edges,
- said insert having crimped surfaces on opposite legs of the U and spanning said ribs whereby said insert may be slid along said ribs into said vane to form a longitudinal baflie
- cap spaced from said insert at its other end for permitting discharge of fluid from said longitudinal passage to the other side of the baflie
- a fluid directing element for turbomachinery comprising, a hollow airfoil vane having leading and trailing edges,
- said insert having crimped surfaces on opposite legs of the U and spanning said ribs whereby said insert may be slid along said ribs into said vane to form a longitudinal baflie
- said insert has tab means at one end thereof to limit its extension into said vane.
- a fluid directing element for turbomachinery comprising,
- each insert extending lengthwise of said vane internally thereof from one end
- each insert having crimped surfaces on opposite legs of the U and spanning a pair of said ribs whereby said insert may be slid along said ribs into said vane to form a longitudinal bafile with a longitudinal passage between the inserts,
- said shorter inserts being disposed to define cross pasages at opposite insert ends respectively
- said blocking means comprising caps across said vane ends
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US540967A US3369792A (en) | 1966-04-07 | 1966-04-07 | Airfoil vane |
DE19661476804 DE1476804A1 (de) | 1966-04-07 | 1966-11-22 | Turbinenschaufel mit Tragflaechenprofil |
GB51495/66A GB1115948A (en) | 1966-04-07 | 1966-11-23 | Improvements in aerofoil vane |
FR86382A FR1504913A (fr) | 1966-04-07 | 1966-12-06 | Ailette profilée creuse, refroidie par une circulation de fluide |
SE17143/66A SE307263B (da) | 1966-04-07 | 1966-12-14 | |
CH5567A CH470575A (de) | 1966-04-07 | 1967-01-04 | Turbinenschaufel |
NL6700156A NL6700156A (da) | 1966-04-07 | 1967-01-05 | |
BE692211D BE692211A (da) | 1966-04-07 | 1967-01-05 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US540967A US3369792A (en) | 1966-04-07 | 1966-04-07 | Airfoil vane |
Publications (1)
Publication Number | Publication Date |
---|---|
US3369792A true US3369792A (en) | 1968-02-20 |
Family
ID=24157651
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US540967A Expired - Lifetime US3369792A (en) | 1966-04-07 | 1966-04-07 | Airfoil vane |
Country Status (8)
Country | Link |
---|---|
US (1) | US3369792A (da) |
BE (1) | BE692211A (da) |
CH (1) | CH470575A (da) |
DE (1) | DE1476804A1 (da) |
FR (1) | FR1504913A (da) |
GB (1) | GB1115948A (da) |
NL (1) | NL6700156A (da) |
SE (1) | SE307263B (da) |
Cited By (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3628885A (en) * | 1969-10-01 | 1971-12-21 | Gen Electric | Fluid-cooled airfoil |
US3630707A (en) * | 1969-06-11 | 1971-12-28 | Corning Glass Works | Temperature control system for glass-shaping molds |
US4019831A (en) * | 1974-09-05 | 1977-04-26 | Brown Boveri Sulzer Turbomachinery Ltd. | Cooled rotor blade for a gas turbine |
US4025226A (en) * | 1975-10-03 | 1977-05-24 | United Technologies Corporation | Air cooled turbine vane |
US4063851A (en) * | 1975-12-22 | 1977-12-20 | United Technologies Corporation | Coolable turbine airfoil |
US4073599A (en) * | 1976-08-26 | 1978-02-14 | Westinghouse Electric Corporation | Hollow turbine blade tip closure |
US4153386A (en) * | 1974-12-11 | 1979-05-08 | United Technologies Corporation | Air cooled turbine vanes |
US4257734A (en) * | 1978-03-22 | 1981-03-24 | Rolls-Royce Limited | Guide vanes for gas turbine engines |
US4456428A (en) * | 1979-10-26 | 1984-06-26 | S.N.E.C.M.A. | Apparatus for cooling turbine blades |
US4930980A (en) * | 1989-02-15 | 1990-06-05 | Westinghouse Electric Corp. | Cooled turbine vane |
US5407321A (en) * | 1993-11-29 | 1995-04-18 | United Technologies Corporation | Damping means for hollow stator vane airfoils |
US6132169A (en) * | 1998-12-18 | 2000-10-17 | General Electric Company | Turbine airfoil and methods for airfoil cooling |
US6238182B1 (en) * | 1999-02-19 | 2001-05-29 | Meyer Tool, Inc. | Joint for a turbine component |
DE19963716A1 (de) * | 1999-12-29 | 2001-07-05 | Alstom Power Schweiz Ag Baden | Gekühlte Strömungsumlenkvorrichtung für eine bei hohen Temperaturen arbeitende Strömungsmaschine |
US6386827B2 (en) | 1999-08-11 | 2002-05-14 | General Electric Company | Nozzle airfoil having movable nozzle ribs |
WO2003085235A1 (de) * | 2002-04-08 | 2003-10-16 | Siemens Aktiengesellschaft | Turbinenschaufel |
EP1355042A2 (de) * | 2002-04-18 | 2003-10-22 | Siemens Aktiengesellschaft | Turbinenschaufel |
US20030219338A1 (en) * | 2002-05-23 | 2003-11-27 | Heyward John Peter | Methods and apparatus for extending gas turbine engine airfoils useful life |
US6746209B2 (en) | 2002-05-31 | 2004-06-08 | General Electric Company | Methods and apparatus for cooling gas turbine engine nozzle assemblies |
US20040208744A1 (en) * | 2003-04-15 | 2004-10-21 | Baolan Shi | Complementary cooled turbine nozzle |
US20050031445A1 (en) * | 2003-08-08 | 2005-02-10 | Siemens Westinghouse Power Corporation | Cooling system for a turbine vane |
US20050047906A1 (en) * | 2003-09-02 | 2005-03-03 | Mcrae Ronald Eugene | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US20050095128A1 (en) * | 2003-10-31 | 2005-05-05 | Benjamin Edward D. | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US20050095134A1 (en) * | 2003-10-31 | 2005-05-05 | Zhang Xiuzhang J. | Methods and apparatus for cooling gas turbine rotor blades |
US20060140762A1 (en) * | 2004-12-23 | 2006-06-29 | United Technologies Corporation | Turbine airfoil cooling passageway |
US20080170944A1 (en) * | 2007-01-11 | 2008-07-17 | Propheter-Hinckley Tracy A | Insertable impingement rib |
US20100209237A1 (en) * | 2009-02-16 | 2010-08-19 | Rolls-Roycs Plc | Vane |
US7824150B1 (en) * | 2009-05-15 | 2010-11-02 | Florida Turbine Technologies, Inc. | Multiple piece turbine airfoil |
US8702375B1 (en) * | 2011-05-19 | 2014-04-22 | Florida Turbine Technologies, Inc. | Turbine stator vane |
US9194632B2 (en) | 2010-01-15 | 2015-11-24 | Ifly Holdings, Llc | Wind tunnel turning vane heat exchanger |
US20160090846A1 (en) * | 2013-06-04 | 2016-03-31 | United Technologies Corporation | Gas turbine engine airfoil trailing edge suction side cooling |
US20170122111A1 (en) * | 2015-11-04 | 2017-05-04 | General Electric Company | Turbine airfoil internal core profile |
US20190048726A1 (en) * | 2017-08-14 | 2019-02-14 | United Technologies Corporation | Expansion seals for airfoils |
US10408090B2 (en) * | 2016-11-17 | 2019-09-10 | United Technologies Corporation | Gas turbine engine article with panel retained by preloaded compliant member |
US11242760B2 (en) * | 2020-01-22 | 2022-02-08 | General Electric Company | Turbine rotor blade with integral impingement sleeve by additive manufacture |
US20220307378A1 (en) * | 2021-03-29 | 2022-09-29 | Raytheon Technologies Corporation | Airfoil assembly with fiber-reinforced composite rings |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4236870A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Turbine blade |
GB9402442D0 (en) * | 1994-02-09 | 1994-04-20 | Rolls Royce Plc | Cooling air cooled gas turbine aerofoil |
US5507621A (en) * | 1995-01-30 | 1996-04-16 | Rolls-Royce Plc | Cooling air cooled gas turbine aerofoil |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2801071A (en) * | 1952-01-31 | 1957-07-30 | Westinghouse Electric Corp | Bladed rotor construction |
US2801073A (en) * | 1952-06-30 | 1957-07-30 | United Aircraft Corp | Hollow sheet metal blade or vane construction |
US2817490A (en) * | 1951-10-10 | 1957-12-24 | Gen Motors Corp | Turbine bucket with internal fins |
US2840298A (en) * | 1954-08-09 | 1958-06-24 | Gen Motors Corp | Heated compressor vane |
US2859011A (en) * | 1953-07-27 | 1958-11-04 | Gen Motors Corp | Turbine bucket and liner |
US2866616A (en) * | 1951-03-02 | 1958-12-30 | Stalker Dev Company | Fabricated bladed structures for axial flow machines |
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
US2906495A (en) * | 1955-04-29 | 1959-09-29 | Eugene F Schum | Turbine blade with corrugated strut |
US2923525A (en) * | 1958-04-04 | 1960-02-02 | Orenda Engines Ltd | Hollow gas turbine blade |
US3095180A (en) * | 1959-03-05 | 1963-06-25 | Stalker Corp | Blades for compressors, turbines and the like |
-
1966
- 1966-04-07 US US540967A patent/US3369792A/en not_active Expired - Lifetime
- 1966-11-22 DE DE19661476804 patent/DE1476804A1/de active Pending
- 1966-11-23 GB GB51495/66A patent/GB1115948A/en not_active Expired
- 1966-12-06 FR FR86382A patent/FR1504913A/fr not_active Expired
- 1966-12-14 SE SE17143/66A patent/SE307263B/xx unknown
-
1967
- 1967-01-04 CH CH5567A patent/CH470575A/de not_active IP Right Cessation
- 1967-01-05 NL NL6700156A patent/NL6700156A/xx unknown
- 1967-01-05 BE BE692211D patent/BE692211A/xx unknown
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
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US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2866616A (en) * | 1951-03-02 | 1958-12-30 | Stalker Dev Company | Fabricated bladed structures for axial flow machines |
US2817490A (en) * | 1951-10-10 | 1957-12-24 | Gen Motors Corp | Turbine bucket with internal fins |
US2801071A (en) * | 1952-01-31 | 1957-07-30 | Westinghouse Electric Corp | Bladed rotor construction |
US2801073A (en) * | 1952-06-30 | 1957-07-30 | United Aircraft Corp | Hollow sheet metal blade or vane construction |
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
US2859011A (en) * | 1953-07-27 | 1958-11-04 | Gen Motors Corp | Turbine bucket and liner |
US2840298A (en) * | 1954-08-09 | 1958-06-24 | Gen Motors Corp | Heated compressor vane |
US2906495A (en) * | 1955-04-29 | 1959-09-29 | Eugene F Schum | Turbine blade with corrugated strut |
US2923525A (en) * | 1958-04-04 | 1960-02-02 | Orenda Engines Ltd | Hollow gas turbine blade |
US3095180A (en) * | 1959-03-05 | 1963-06-25 | Stalker Corp | Blades for compressors, turbines and the like |
Cited By (58)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3630707A (en) * | 1969-06-11 | 1971-12-28 | Corning Glass Works | Temperature control system for glass-shaping molds |
US3628885A (en) * | 1969-10-01 | 1971-12-21 | Gen Electric | Fluid-cooled airfoil |
US4019831A (en) * | 1974-09-05 | 1977-04-26 | Brown Boveri Sulzer Turbomachinery Ltd. | Cooled rotor blade for a gas turbine |
US4153386A (en) * | 1974-12-11 | 1979-05-08 | United Technologies Corporation | Air cooled turbine vanes |
US4025226A (en) * | 1975-10-03 | 1977-05-24 | United Technologies Corporation | Air cooled turbine vane |
US4063851A (en) * | 1975-12-22 | 1977-12-20 | United Technologies Corporation | Coolable turbine airfoil |
US4073599A (en) * | 1976-08-26 | 1978-02-14 | Westinghouse Electric Corporation | Hollow turbine blade tip closure |
US4257734A (en) * | 1978-03-22 | 1981-03-24 | Rolls-Royce Limited | Guide vanes for gas turbine engines |
US4456428A (en) * | 1979-10-26 | 1984-06-26 | S.N.E.C.M.A. | Apparatus for cooling turbine blades |
US4930980A (en) * | 1989-02-15 | 1990-06-05 | Westinghouse Electric Corp. | Cooled turbine vane |
AU623213B2 (en) * | 1989-02-15 | 1992-05-07 | Westinghouse Electric Corporation | Cooled turbine vane |
US5407321A (en) * | 1993-11-29 | 1995-04-18 | United Technologies Corporation | Damping means for hollow stator vane airfoils |
US6132169A (en) * | 1998-12-18 | 2000-10-17 | General Electric Company | Turbine airfoil and methods for airfoil cooling |
US6238182B1 (en) * | 1999-02-19 | 2001-05-29 | Meyer Tool, Inc. | Joint for a turbine component |
US6386827B2 (en) | 1999-08-11 | 2002-05-14 | General Electric Company | Nozzle airfoil having movable nozzle ribs |
DE19963716A1 (de) * | 1999-12-29 | 2001-07-05 | Alstom Power Schweiz Ag Baden | Gekühlte Strömungsumlenkvorrichtung für eine bei hohen Temperaturen arbeitende Strömungsmaschine |
US6419449B2 (en) | 1999-12-29 | 2002-07-16 | Alstom (Switzerland) Ltd | Cooled flow deflection apparatus for a fluid-flow machine which operates at high temperatures |
EP1113144A3 (de) * | 1999-12-29 | 2004-05-19 | ALSTOM Technology Ltd | Gekühlte Strömungsumlenkvorrichtung für eine bei hohen Temperaturen arbeitende Strömungsmaschhine |
WO2003085235A1 (de) * | 2002-04-08 | 2003-10-16 | Siemens Aktiengesellschaft | Turbinenschaufel |
EP1355042A2 (de) * | 2002-04-18 | 2003-10-22 | Siemens Aktiengesellschaft | Turbinenschaufel |
US20040022629A1 (en) * | 2002-04-18 | 2004-02-05 | Peter Tiemann | Turbine blade or vane |
EP1355042A3 (de) * | 2002-04-18 | 2005-03-30 | Siemens Aktiengesellschaft | Turbinenschaufel |
US20030219338A1 (en) * | 2002-05-23 | 2003-11-27 | Heyward John Peter | Methods and apparatus for extending gas turbine engine airfoils useful life |
US6932570B2 (en) | 2002-05-23 | 2005-08-23 | General Electric Company | Methods and apparatus for extending gas turbine engine airfoils useful life |
US6746209B2 (en) | 2002-05-31 | 2004-06-08 | General Electric Company | Methods and apparatus for cooling gas turbine engine nozzle assemblies |
US6884036B2 (en) * | 2003-04-15 | 2005-04-26 | General Electric Company | Complementary cooled turbine nozzle |
JP2004316654A (ja) * | 2003-04-15 | 2004-11-11 | General Electric Co <Ge> | 補完冷却式タービンノズル |
JP4728588B2 (ja) * | 2003-04-15 | 2011-07-20 | ゼネラル・エレクトリック・カンパニイ | 補完冷却式タービンノズル |
US20040208744A1 (en) * | 2003-04-15 | 2004-10-21 | Baolan Shi | Complementary cooled turbine nozzle |
US6955523B2 (en) * | 2003-08-08 | 2005-10-18 | Siemens Westinghouse Power Corporation | Cooling system for a turbine vane |
US20050031445A1 (en) * | 2003-08-08 | 2005-02-10 | Siemens Westinghouse Power Corporation | Cooling system for a turbine vane |
US20050047906A1 (en) * | 2003-09-02 | 2005-03-03 | Mcrae Ronald Eugene | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US6923616B2 (en) | 2003-09-02 | 2005-08-02 | General Electric Company | Methods and apparatus for cooling gas turbine engine rotor assemblies |
US6984112B2 (en) | 2003-10-31 | 2006-01-10 | General Electric Company | Methods and apparatus for cooling gas turbine rotor blades |
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Also Published As
Publication number | Publication date |
---|---|
CH470575A (de) | 1969-03-31 |
NL6700156A (da) | 1967-10-09 |
FR1504913A (fr) | 1967-12-08 |
GB1115948A (en) | 1968-06-06 |
BE692211A (da) | 1967-07-05 |
DE1476804A1 (de) | 1970-03-26 |
SE307263B (da) | 1968-12-23 |
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