SU670237A3 - Liquid-cooled rotor - Google Patents
Liquid-cooled rotorInfo
- Publication number
- SU670237A3 SU670237A3 SU731962218A SU1962218A SU670237A3 SU 670237 A3 SU670237 A3 SU 670237A3 SU 731962218 A SU731962218 A SU 731962218A SU 1962218 A SU1962218 A SU 1962218A SU 670237 A3 SU670237 A3 SU 670237A3
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- blades
- cooling
- rotor
- disk
- channels
- Prior art date
Links
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F01D5/185—Liquid cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Description
(54) РОТОР С ЖИДКОСТНЫМ ОХЛАЖДЕНИЕМ(54) LIQUID COOLING ROTOR
Изобретение относитс к области турбостроени и может быть использовано дл высокотемпературных газовых турбин.This invention relates to the field of turbine engineering and can be used for high temperature gas turbines.
Наиболее близким к предложенному по технической сущности вл етс ротор с жидкостным охлаждением, преимущественно газовой турбины, содержащий диск с лопатками на периферии, расположенную у корн лопаток кольцевую платформу, образующую с диском резервуар, сообщенный на входе с полостью подвода охлаждающей жидкости, выполненной в диске, а на выходе - с незамкнутым контуром распределени , имеющим охлаждающие каналы, выполненные в лопатках, дозаторы дл распределени жидкости по каналам охлаждени 1 .Closest to the proposed technical essence is a rotor with liquid cooling, mainly a gas turbine, which contains a disk with blades on the periphery, an annular platform located at the root of the blades, which forms a reservoir with the disk, which communicates at the entrance with a coolant supply cavity made in the disk, and at the outlet - with an open distribution circuit, having cooling channels made in the blades, dispensers for distributing liquid through the cooling channels 1.
Недостатком такого ротора вл етс малоэффективное охлаждение лопаток.The disadvantage of such a rotor is inefficient cooling of the blades.
Целью изобретени вл етс повыщение эффективности охлаждени лопаток.The aim of the invention is to increase the cooling efficiency of the blades.
Это достигаетс тем, что в предложенном роторе полость подвода сообщена с резервуаром трубками, выходные отверсти которых направлены по радиусу от оси вращени .This is achieved by the fact that in the proposed rotor the supply cavity is in communication with the reservoir by tubes whose outlet openings are radially directed from the axis of rotation.
В верхней части лопаток могут быть размещены поперечные патрубки и выходные каналы, сообщенные с внещними концами охлаждающих каналов, а на выходе трубок - выступы, контактирующие с нижней стороной платформы.In the upper part of the blades can be placed transverse nozzles and outlet channels communicated with the outer ends of the cooling channels, and at the outlet of the tubes - protrusions in contact with the underside of the platform.
На фиг. 1 схематически изображен предложенный ротор, общий вид; на фиг. 2 - то же, продольный разрез; на фиг. 3 - то же, поперечный разрез; ,на фиг. 4 -FIG. 1 schematically shows the proposed rotor, a general view; in fig. 2 - the same, longitudinal section; in fig. 3 - the same cross section; in FIG. four -
ротор с елочным замковым соединением.rotor with fir-tree locking connection.
Ротор газовой турбины с жидкостным охлаждением содержит диск 1 с лопатками 2 на периферии, расположенную у корн лопаток 2 кольцевую платформу 3, образующую с диском 1 резервуар 4, сообщенный на входе с полостью 5с подвода охлаждающей жидкости, выполненной в диске 1. Резервуар 4 на выходе-сообщен с каналами 6, выполненными в лопатке 2, и имеет дозатор 7 дл распределени жидкости по этим каналам . Полость 5 подвода охлаждающей жидкости сообщена с резервуаром 4 трубками 8, выходные отверсти которых направлены по радиусу от оси вращени .The rotor of a gas turbine with liquid cooling contains a disk 1 with blades 2 on the periphery, located at the root of the blades 2 annular platform 3, which forms with the disk 1 a reservoir 4 communicated at the entrance with the cavity 5c of the coolant supply made in disk 1. The reservoir 4 at the exit - communicated with the channels 6 formed in the blade 2, and has a dispenser 7 for distributing liquid through these channels. The coolant supply cavity 5 communicates with the reservoir 4 by tubes 8, the outlet openings of which are directed along the radius from the axis of rotation.
В верхней части лопаток 2 расположены поперечные патрубки 9 и выходные каналы 10, которые сообщены с внешними концами охлаждающих каналов 6. На выходе трубки 8 имеют выступы 11, контактирующие с нижней стороной платформы 3. В корпусе 12 турбины выполнены кольцевые канавки 13.In the upper part of the blades 2 there are transverse nozzles 9 and output channels 10, which communicate with the outer ends of the cooling channels 6. At the outlet, the tubes 8 have protrusions 11 in contact with the underside of the platform 3. The annular grooves 13 are made in the turbine casing 12.
В роторе с елочным замковым соединением резервуар 4 образован внешней поверхностью полки лопатки 2 и кольцевой платформой 3, а полость 5 - внутренней поверхностью полки лопатки 2 и внешней поверхностью диска 1. В теле диска 1 также расположены каналы 14 дл поступлени охлаждающей жидкости в полость 5. In the rotor with the fir-tree locking connection, the reservoir 4 is formed by the outer surface of the shelf of the blade 2 and the ring platform 3, and cavity 5 is the inner surface of the shelf of the blade 2 and the outer surface of the disk 1. In the body of the disk 1 there are also channels 14 for coolant to enter the cavity 5.
Ротор работает следующим образом.The rotor operates as follows.
Охлаждающа жидкость (обычно вода) при низком давлении подаетс в полость 5, приобретает скорость, с которой вращаетс обод диска, и непрерывно по трубкам 8 поступает в резервуар 4. Отсюда охлаждающа жидкость проходит поверх дозатора 7 в радиально направленные концы каналов 6 охлаждени и поступает в патрубки 9. Истекающа из выходных каналов 10 охлаждающа жидкость поступает в кольцевую канавку 13, выполненную в корпусе 12 турбины .Cooling fluid (usually water) at low pressure flows into cavity 5, acquires the speed with which the disk rim rotates, and continuously flows through tubes 8 into reservoir 4. From here, cooling fluid passes over dispenser 7 into radially directed ends of cooling channels 6 and enters nozzles 9. The cooling fluid flowing out of the outlet channels 10 flows into an annular groove 13 formed in the turbine housing 12.
Такое выполнение ротора позвол ет уменьшить расход охлаждающей жидкости и повысить эффективность охлаждени лопаток .This embodiment of the rotor allows to reduce the coolant flow rate and increase the cooling efficiency of the blades.
Claims (3)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00285633A US3804551A (en) | 1972-09-01 | 1972-09-01 | System for the introduction of coolant into open-circuit cooled turbine buckets |
Publications (1)
Publication Number | Publication Date |
---|---|
SU670237A3 true SU670237A3 (en) | 1979-06-25 |
Family
ID=23095081
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU731962218A SU670237A3 (en) | 1972-09-01 | 1973-08-31 | Liquid-cooled rotor |
Country Status (9)
Country | Link |
---|---|
US (1) | US3804551A (en) |
JP (1) | JPS5644241B2 (en) |
DE (1) | DE2336952C2 (en) |
FR (1) | FR2198052B1 (en) |
GB (1) | GB1437618A (en) |
IT (1) | IT993116B (en) |
NL (1) | NL7311237A (en) |
NO (1) | NO143880C (en) |
SU (1) | SU670237A3 (en) |
Families Citing this family (38)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4017210A (en) * | 1976-02-19 | 1977-04-12 | General Electric Company | Liquid-cooled turbine bucket with integral distribution and metering system |
US4111604A (en) * | 1976-07-12 | 1978-09-05 | General Electric Company | Bucket tip construction for open circuit liquid cooled turbines |
US4130373A (en) * | 1976-11-15 | 1978-12-19 | General Electric Company | Erosion suppression for liquid-cooled gas turbines |
US4119390A (en) * | 1976-11-19 | 1978-10-10 | General Electric Company | Liquid-cooled, turbine bucket with enhanced heat transfer performance |
US4090810A (en) * | 1977-03-23 | 1978-05-23 | General Electric Company | Liquid-cooled turbine bucket with enhanced heat transfer performance |
US4212587A (en) * | 1978-05-30 | 1980-07-15 | General Electric Company | Cooling system for a gas turbine using V-shaped notch weirs |
US4835958A (en) * | 1978-10-26 | 1989-06-06 | Rice Ivan G | Process for directing a combustion gas stream onto rotatable blades of a gas turbine |
US4545197A (en) * | 1978-10-26 | 1985-10-08 | Rice Ivan G | Process for directing a combustion gas stream onto rotatable blades of a gas turbine |
US4260336A (en) * | 1978-12-21 | 1981-04-07 | United Technologies Corporation | Coolant flow control apparatus for rotating heat exchangers with supercritical fluids |
US4244676A (en) * | 1979-06-01 | 1981-01-13 | General Electric Company | Cooling system for a gas turbine using a cylindrical insert having V-shaped notch weirs |
US4242045A (en) * | 1979-06-01 | 1980-12-30 | General Electric Company | Trap seal for open circuit liquid cooled turbines |
US4350473A (en) * | 1980-02-22 | 1982-09-21 | General Electric Company | Liquid cooled counter flow turbine bucket |
US4512715A (en) * | 1980-07-22 | 1985-04-23 | Electric Power Research Institute, Inc. | Method and means for recapturing coolant in a gas turbine |
GB2082257B (en) * | 1980-08-08 | 1984-02-15 | Gen Electric | Liquid coolant distribution systems for gas turbines |
US4531889A (en) * | 1980-08-08 | 1985-07-30 | General Electric Co. | Cooling system utilizing flow resistance devices to distribute liquid coolant to air foil distribution channels |
US4565490A (en) * | 1981-06-17 | 1986-01-21 | Rice Ivan G | Integrated gas/steam nozzle |
US4543781A (en) * | 1981-06-17 | 1985-10-01 | Rice Ivan G | Annular combustor for gas turbine |
EP0340149B1 (en) * | 1988-04-25 | 1993-05-19 | United Technologies Corporation | Dirt removal means for air cooled blades |
US5030060A (en) * | 1988-10-20 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method and apparatus for cooling high temperature ceramic turbine blade portions |
JPH10238301A (en) * | 1997-02-21 | 1998-09-08 | Mitsubishi Heavy Ind Ltd | Cooling passage of gas turbine blade |
CA2242650C (en) * | 1997-07-07 | 2001-10-16 | Yukihiro Hashimoto | Gas turbine moving blade steam cooling system |
WO1999060253A1 (en) * | 1998-05-18 | 1999-11-25 | Siemens Aktiengesellschaft | Cooled turbine blade platform |
DE19921644B4 (en) | 1999-05-10 | 2012-01-05 | Alstom | Coolable blade for a gas turbine |
DE19926949B4 (en) * | 1999-06-14 | 2011-01-05 | Alstom | Cooling arrangement for blades of a gas turbine |
DE60045026D1 (en) * | 1999-09-24 | 2010-11-11 | Gen Electric | Gas turbine blade with impact cooled platform |
DE19963099B4 (en) | 1999-12-24 | 2014-01-02 | Alstom Technology Ltd. | Cooling air holes in gas turbine components |
GB2365930B (en) * | 2000-08-12 | 2004-12-08 | Rolls Royce Plc | A turbine blade support assembly and a turbine assembly |
EP1456505A1 (en) * | 2001-12-10 | 2004-09-15 | ALSTOM Technology Ltd | Thermally loaded component |
US6832893B2 (en) | 2002-10-24 | 2004-12-21 | Pratt & Whitney Canada Corp. | Blade passive cooling feature |
US7766606B2 (en) * | 2006-08-17 | 2010-08-03 | Siemens Energy, Inc. | Turbine airfoil cooling system with platform cooling channels with diffusion slots |
CH704716A1 (en) * | 2011-03-22 | 2012-09-28 | Alstom Technology Ltd | Rotor disk for a turbine rotor and turbine as well as with such a rotor disk. |
US8622701B1 (en) * | 2011-04-21 | 2014-01-07 | Florida Turbine Technologies, Inc. | Turbine blade platform with impingement cooling |
US9982542B2 (en) | 2014-07-21 | 2018-05-29 | United Technologies Corporation | Airfoil platform impingement cooling holes |
US9835087B2 (en) * | 2014-09-03 | 2017-12-05 | General Electric Company | Turbine bucket |
US10156145B2 (en) * | 2015-10-27 | 2018-12-18 | General Electric Company | Turbine bucket having cooling passageway |
US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
US10822987B1 (en) * | 2019-04-16 | 2020-11-03 | Pratt & Whitney Canada Corp. | Turbine stator outer shroud cooling fins |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2991973A (en) * | 1954-10-18 | 1961-07-11 | Parsons & Marine Eng Turbine | Cooling of bodies subject to a hot gas stream |
US2931623A (en) * | 1957-05-02 | 1960-04-05 | Orenda Engines Ltd | Gas turbine rotor assembly |
US3446482A (en) * | 1967-03-24 | 1969-05-27 | Gen Electric | Liquid cooled turbine rotor |
US3446481A (en) * | 1967-03-24 | 1969-05-27 | Gen Electric | Liquid cooled turbine rotor |
DE1801475B2 (en) * | 1968-10-05 | 1971-08-12 | Daimler Benz Ag, 7000 Stuttgart | AIR-COOLED TURBINE BLADE |
US3658439A (en) * | 1970-11-27 | 1972-04-25 | Gen Electric | Metering of liquid coolant in open-circuit liquid-cooled gas turbines |
US3736071A (en) * | 1970-11-27 | 1973-05-29 | Gen Electric | Bucket tip/collection slot combination for open-circuit liquid-cooled gas turbines |
-
1972
- 1972-09-01 US US00285633A patent/US3804551A/en not_active Expired - Lifetime
-
1973
- 1973-07-20 DE DE2336952A patent/DE2336952C2/en not_active Expired
- 1973-08-15 NL NL7311237A patent/NL7311237A/xx not_active Application Discontinuation
- 1973-08-16 GB GB3882373A patent/GB1437618A/en not_active Expired
- 1973-08-29 NO NO3395/73A patent/NO143880C/en unknown
- 1973-08-30 FR FR7331421A patent/FR2198052B1/fr not_active Expired
- 1973-08-31 IT IT28454/73A patent/IT993116B/en active
- 1973-08-31 SU SU731962218A patent/SU670237A3/en active
- 1973-08-31 JP JP9740073A patent/JPS5644241B2/ja not_active Expired
Also Published As
Publication number | Publication date |
---|---|
US3804551A (en) | 1974-04-16 |
NL7311237A (en) | 1974-03-05 |
NO143880B (en) | 1981-01-19 |
DE2336952C2 (en) | 1983-12-15 |
FR2198052A1 (en) | 1974-03-29 |
NO143880C (en) | 1981-04-29 |
JPS5644241B2 (en) | 1981-10-19 |
DE2336952A1 (en) | 1974-03-14 |
JPS4992413A (en) | 1974-09-03 |
IT993116B (en) | 1975-09-30 |
FR2198052B1 (en) | 1974-11-08 |
GB1437618A (en) | 1976-06-03 |
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