GB1441969A - Impingement cooled turbine blades and method of making same - Google Patents
Impingement cooled turbine blades and method of making sameInfo
- Publication number
- GB1441969A GB1441969A GB5024273A GB5024273A GB1441969A GB 1441969 A GB1441969 A GB 1441969A GB 5024273 A GB5024273 A GB 5024273A GB 5024273 A GB5024273 A GB 5024273A GB 1441969 A GB1441969 A GB 1441969A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- insert
- holes
- cooling air
- impingement
- 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
Links
Classifications
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
-
- 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
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1441969 Turbine blades AVCO CORP 29 Oct 1973 [31 Oct 1972] 50242/73 Heading FIT Cooling of turbine rotor blades 12 is effected by impingement of cooling air on the internal surface of the blade via holes 48 in a thin-walled insert retained in the hollow aerofoil section of the blade by means of a pin 36 inserted through holes in a lug 34 in the blade root 14 and in the solid end 30 of the insert. After insertion, the end of the pin is flared by a tool inserted through an aligned hole 38. The cooling air is fed from a compressor via a passage (20), Fig. 1, (not shown) in the rotor and in to the cut-away sides of the blade in the root passage 28. The insert tip, and the blade tip, are sealed by an end-cap 40 having a flared flange 41 welded or brazed to the insert and retained by engagement under a lip 42 in the blade tip. The holes 48 are directed at the inside leading edge of the blade, and further holes (50), (52), Fig. 5, (not shown), are provided in the sides and trailing edges of the insert. Pins 46 integral with the blade define flow-paths from the cooling air after impingement to allow its release from the blade interior via a trailing edge (56), also having integral pins (54).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00302421A US3846041A (en) | 1972-10-31 | 1972-10-31 | Impingement cooled turbine blades and method of making same |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1441969A true GB1441969A (en) | 1976-07-07 |
Family
ID=23167669
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB5024273A Expired GB1441969A (en) | 1972-10-31 | 1973-10-29 | Impingement cooled turbine blades and method of making same |
Country Status (6)
Country | Link |
---|---|
US (1) | US3846041A (en) |
JP (1) | JPS5249085B2 (en) |
FR (1) | FR2205097A5 (en) |
GB (1) | GB1441969A (en) |
IT (1) | IT997587B (en) |
SE (1) | SE389162B (en) |
Families Citing this family (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH582305A5 (en) * | 1974-09-05 | 1976-11-30 | Bbc Sulzer Turbomaschinen | |
JPS5234111A (en) * | 1975-09-10 | 1977-03-15 | Toshiba Corp | Turbine moving blade |
US3994622A (en) * | 1975-11-24 | 1976-11-30 | United Technologies Corporation | Coolable turbine blade |
GB1564608A (en) * | 1975-12-20 | 1980-04-10 | Rolls Royce | Means for cooling a surface by the impingement of a cooling fluid |
GB1551678A (en) * | 1978-03-20 | 1979-08-30 | Rolls Royce | Cooled rotor blade for a gas turbine engine |
GB1552536A (en) * | 1977-05-05 | 1979-09-12 | Rolls Royce | Rotor blade for a gas turbine engine |
US4297077A (en) * | 1979-07-09 | 1981-10-27 | Westinghouse Electric Corp. | Cooled turbine vane |
US4314794A (en) * | 1979-10-25 | 1982-02-09 | Westinghouse Electric Corp. | Transpiration cooled blade for a gas turbine engine |
US4400137A (en) * | 1980-12-29 | 1983-08-23 | Elliott Turbomachinery Co., Inc. | Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom |
US4451959A (en) * | 1980-12-29 | 1984-06-05 | Elliott Turbomachinery Company, Inc. | Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom |
US4407632A (en) * | 1981-06-26 | 1983-10-04 | United Technologies Corporation | Airfoil pedestaled trailing edge region cooling configuration |
US5352091A (en) * | 1994-01-05 | 1994-10-04 | United Technologies Corporation | Gas turbine airfoil |
DE4430302A1 (en) * | 1994-08-26 | 1996-02-29 | Abb Management Ag | Impact-cooled wall part |
US5741117A (en) * | 1996-10-22 | 1998-04-21 | United Technologies Corporation | Method for cooling a gas turbine stator vane |
US6193465B1 (en) * | 1998-09-28 | 2001-02-27 | General Electric Company | Trapped insert turbine airfoil |
US6453557B1 (en) * | 2000-04-11 | 2002-09-24 | General Electric Company | Method of joining a vane cavity insert to a nozzle segment of a gas turbine |
US6811378B2 (en) * | 2002-07-31 | 2004-11-02 | Power Systems Mfg, Llc | Insulated cooling passageway for cooling a shroud of a turbine blade |
US6769877B2 (en) * | 2002-10-18 | 2004-08-03 | General Electric Company | Undercut leading edge for compressor blades and related method |
US6824352B1 (en) * | 2003-09-29 | 2004-11-30 | Power Systems Mfg, Llc | Vane enhanced trailing edge cooling design |
US7118326B2 (en) * | 2004-06-17 | 2006-10-10 | Siemens Power Generation, Inc. | Cooled gas turbine vane |
FR2899271B1 (en) | 2006-03-29 | 2008-05-30 | Snecma Sa | DUSTBOARD AND COOLING SHIELD ASSEMBLY, TURBOMACHINE DISPENSER COMPRISING THE ASSEMBLY, TURBOMACHINE, METHOD OF ASSEMBLING AND REPAIRING THE ASSEMBLY |
DE102007012320A1 (en) * | 2007-03-09 | 2008-09-11 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine blade with blade-formed microturbine nozzle |
US7713029B1 (en) | 2007-03-28 | 2010-05-11 | Florida Turbine Technologies, Inc. | Turbine blade with spar and shell construction |
US7972113B1 (en) * | 2007-05-02 | 2011-07-05 | Florida Turbine Technologies, Inc. | Integral turbine blade and platform |
US8070421B2 (en) * | 2008-03-26 | 2011-12-06 | Siemens Energy, Inc. | Mechanically affixed turbine shroud plug |
US8033790B2 (en) * | 2008-09-26 | 2011-10-11 | Siemens Energy, Inc. | Multiple piece turbine engine airfoil with a structural spar |
US7967565B1 (en) * | 2009-03-20 | 2011-06-28 | Florida Turbine Technologies, Inc. | Low cooling flow turbine blade |
US8449249B2 (en) | 2010-04-09 | 2013-05-28 | Williams International Co., L.L.C. | Turbine nozzle apparatus and associated method of manufacture |
US8888455B2 (en) * | 2010-11-10 | 2014-11-18 | Rolls-Royce Corporation | Gas turbine engine and blade for gas turbine engine |
US9759072B2 (en) | 2012-08-30 | 2017-09-12 | United Technologies Corporation | Gas turbine engine airfoil cooling circuit arrangement |
US9670797B2 (en) | 2012-09-28 | 2017-06-06 | United Technologies Corporation | Modulated turbine vane cooling |
US20150198050A1 (en) * | 2014-01-15 | 2015-07-16 | Siemens Energy, Inc. | Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine |
WO2016036366A1 (en) * | 2014-09-04 | 2016-03-10 | Siemens Aktiengesellschaft | Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of a gas turbine airfoil |
EP3189214A1 (en) | 2014-09-04 | 2017-07-12 | Siemens Aktiengesellschaft | Internal cooling system with insert forming nearwall cooling channels in midchord cooling cavities of a gas turbine airfoil |
US10443407B2 (en) * | 2016-02-15 | 2019-10-15 | General Electric Company | Accelerator insert for a gas turbine engine airfoil |
DE102016216858A1 (en) * | 2016-09-06 | 2018-03-08 | Rolls-Royce Deutschland Ltd & Co Kg | Blade for a turbomachine and method for assembling a blade for a turbomachine |
US10626740B2 (en) | 2016-12-08 | 2020-04-21 | General Electric Company | Airfoil trailing edge segment |
FR3067389B1 (en) * | 2017-04-10 | 2021-10-29 | Safran | TURBINE BLADE WITH AN IMPROVED STRUCTURE |
US10851663B2 (en) * | 2017-06-12 | 2020-12-01 | General Electric Company | Turbomachine rotor blade |
FR3114762B1 (en) * | 2020-10-06 | 2022-08-19 | Safran Aircraft Engines | Method of manufacturing a turbomachine compressor blade by compacting |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2779565A (en) * | 1948-01-05 | 1957-01-29 | Bruno W Bruckmann | Air cooling of turbine blades |
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
DE926397C (en) * | 1952-09-25 | 1955-04-18 | Ernst Heinkel Dr Dr | Hollow blade, preferably for axially flowed turbines |
US3446480A (en) * | 1966-12-19 | 1969-05-27 | Gen Motors Corp | Turbine rotor |
US3700348A (en) * | 1968-08-13 | 1972-10-24 | Gen Electric | Turbomachinery blade structure |
US3635587A (en) * | 1970-06-02 | 1972-01-18 | Gen Motors Corp | Blade cooling liner |
-
1972
- 1972-10-31 US US00302421A patent/US3846041A/en not_active Expired - Lifetime
-
1973
- 1973-10-29 GB GB5024273A patent/GB1441969A/en not_active Expired
- 1973-10-30 SE SE7314736A patent/SE389162B/en unknown
- 1973-10-31 IT IT53459/73A patent/IT997587B/en active
- 1973-10-31 JP JP48121871A patent/JPS5249085B2/ja not_active Expired
- 1973-10-31 FR FR7338953A patent/FR2205097A5/fr not_active Expired
Also Published As
Publication number | Publication date |
---|---|
JPS4995011A (en) | 1974-09-10 |
US3846041A (en) | 1974-11-05 |
IT997587B (en) | 1975-12-30 |
FR2205097A5 (en) | 1974-05-24 |
DE2354693A1 (en) | 1974-05-09 |
SE389162B (en) | 1976-10-25 |
JPS5249085B2 (en) | 1977-12-14 |
DE2354693B2 (en) | 1975-07-03 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1441969A (en) | Impingement cooled turbine blades and method of making same | |
GB1458734A (en) | Manufacture of hollow turbomachinery blades | |
GB1530256A (en) | Cooled blade for a gas turbine engine | |
GB1225926A (en) | ||
GB1255360A (en) | Improvements relating to internally cooled turbine blades | |
FR2181407A5 (en) | ||
GB1282796A (en) | Fluid cooled turbine blade | |
GB853328A (en) | Method of and device for cooling the component elements of machines | |
GB1467374A (en) | Hollow turbomachinery blades | |
GB1491556A (en) | Rotor blades for turbomachines | |
GB1277280A (en) | Improvements in turbomachinery blades | |
GB1483976A (en) | Cooled blades for rotodynamic machines | |
KR910018662A (en) | Apparatus and method for airflow cooling at gas turbine bucket trailing edge tips | |
GB1366924A (en) | Compressor blades | |
GB701263A (en) | Improvements in or relating to turbo-machines | |
GB723394A (en) | Improvements in turbine blades | |
GB1419381A (en) | Fan for gas turbine engines | |
GB833770A (en) | Hollow turbine or compressor blades | |
GB1033759A (en) | Aerofoil-shaped blade | |
GB1450133A (en) | Cooling of gas turbine engines | |
GB1471963A (en) | Mould for use in the manufacture of hollow turbine blades and method of use thereof | |
GB1332679A (en) | Turbomachinery blade structure | |
GB811586A (en) | Turbine or compressor blades | |
GB846583A (en) | Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines | |
GB811921A (en) | Improvements relating to manufacture of blading for axial-flow fluid machines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PCNP | Patent ceased through non-payment of renewal fee |