SU358525A1 - Coolable turbine blade - Google Patents
Coolable turbine bladeInfo
- Publication number
- SU358525A1 SU358525A1 SU1496390A SU1496390A SU358525A1 SU 358525 A1 SU358525 A1 SU 358525A1 SU 1496390 A SU1496390 A SU 1496390A SU 1496390 A SU1496390 A SU 1496390A SU 358525 A1 SU358525 A1 SU 358525A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- turbine blade
- blade
- coolable
- coolable turbine
- turbine
- Prior art date
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
Изобретение от1носитс к турбостроению и может быть применено дл высокотемпературных газовых турбин.The invention relates to turbine engineering and can be applied to high temperature gas turbines.
Известны охлаждаемые лопатки турбины, содержащие перо с криволинейными каналами в выходной кромке, входной и выходной участки которых параллельны оси турбины.Known cooled turbine blades, containing a feather with curved channels in the output edge, the input and output sections of which are parallel to the axis of the turbine.
Цель изобретени - повышение интенсивности охлаждени .The purpose of the invention is to increase the intensity of cooling.
В предлатаемом изобретении дл достижени этой целн промежуточный участок канала выполнен наклонным к корню лопатки в направлении потока охлаждающего воздуха.In the present invention, in order to achieve this whole intermediate section of the channel, it is inclined toward the root of the blade in the direction of the flow of cooling air.
На фит. 1 дана предлагаема лопатка, Общий вид; «а фиг. 2 - элемент выходной «ромки .On the fit. 1 dana we offer scapula, General view; “And FIG. 2 - an element of the output "romki.
На выходной кромке пера / лопатки св зующие ребра 2 выполнены в виде тонких пластии . Ребра образуют криволинейные каналы,At the exit edge of the feather / blade, the connecting ribs 2 are made in the form of thin plastia. The ribs form curved channels,
входной 3 и выходной 4 участки которых параллельны оси турбины. Дл повышени интенсивности охлаждени промежуточный участок канала выполнен наклонным к корню лопатки в направлении патока охлаждающего воздуха. При таком выполнении каналов образуютс вторичные течени охлаждающего воздуха, турбулизирующие основной поток.input 3 and output 4 of which are parallel to the axis of the turbine. In order to increase the intensity of cooling, the intermediate section of the channel is made inclined toward the root of the blade in the direction of the flow of cooling air. With this design of the channels, secondary flows of cooling air are formed, which turbulent the main flow.
Предмет изобретени Subject invention
Охлаждаема лопатка турбины, содержаща перо с криволинейными каналами в выходной кромке, входной и выходной участки которых параллельны оси турбины, отличающа с тем, что, с целью повышени интенсивности охлаждени , промежуточный участок канала выполнен наклонным к корню лопатки в направлении потока охлаждающего воздуха.A cooled turbine blade containing a feather with curvilinear channels in the output edge, the inlet and outlet sections of which are parallel to the axis of the turbine, characterized in that, in order to increase the cooling intensity, the intermediate section of the channel is inclined towards the root of the blade in the direction of cooling air flow.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU1496390A SU358525A1 (en) | 1970-12-09 | 1970-12-09 | Coolable turbine blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU1496390A SU358525A1 (en) | 1970-12-09 | 1970-12-09 | Coolable turbine blade |
Publications (1)
Publication Number | Publication Date |
---|---|
SU358525A1 true SU358525A1 (en) | 1972-11-03 |
Family
ID=20460533
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU1496390A SU358525A1 (en) | 1970-12-09 | 1970-12-09 | Coolable turbine blade |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU358525A1 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4180373A (en) * | 1977-12-28 | 1979-12-25 | United Technologies Corporation | Turbine blade |
US4526512A (en) * | 1983-03-28 | 1985-07-02 | General Electric Co. | Cooling flow control device for turbine blades |
US5246341A (en) * | 1992-07-06 | 1993-09-21 | United Technologies Corporation | Turbine blade trailing edge cooling construction |
US5601399A (en) * | 1996-05-08 | 1997-02-11 | Alliedsignal Inc. | Internally cooled gas turbine vane |
US5772397A (en) * | 1996-05-08 | 1998-06-30 | Alliedsignal Inc. | Gas turbine airfoil with aft internal cooling |
EP1213442A1 (en) * | 2000-12-05 | 2002-06-12 | United Technologies Corporation | Coolable airfoil structure |
EP2692991A1 (en) * | 2012-08-01 | 2014-02-05 | Siemens Aktiengesellschaft | Cooling of turbine blades or vanes |
-
1970
- 1970-12-09 SU SU1496390A patent/SU358525A1/en active
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4180373A (en) * | 1977-12-28 | 1979-12-25 | United Technologies Corporation | Turbine blade |
US4526512A (en) * | 1983-03-28 | 1985-07-02 | General Electric Co. | Cooling flow control device for turbine blades |
US5246341A (en) * | 1992-07-06 | 1993-09-21 | United Technologies Corporation | Turbine blade trailing edge cooling construction |
US5601399A (en) * | 1996-05-08 | 1997-02-11 | Alliedsignal Inc. | Internally cooled gas turbine vane |
US5772397A (en) * | 1996-05-08 | 1998-06-30 | Alliedsignal Inc. | Gas turbine airfoil with aft internal cooling |
EP1213442A1 (en) * | 2000-12-05 | 2002-06-12 | United Technologies Corporation | Coolable airfoil structure |
EP2692991A1 (en) * | 2012-08-01 | 2014-02-05 | Siemens Aktiengesellschaft | Cooling of turbine blades or vanes |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3574481A (en) | Variable area cooled airfoil construction for gas turbines | |
US3369792A (en) | Airfoil vane | |
US4178129A (en) | Gas turbine engine cooling system | |
US3902820A (en) | Fluid cooled turbine rotor blade | |
US3628880A (en) | Vane assembly and temperature control arrangement | |
US4541775A (en) | Clearance control in turbine seals | |
US3420502A (en) | Fluid-cooled airfoil | |
GB1357713A (en) | Cooled rotor blades for gas turbines | |
JPS62271902A (en) | Cooled blade for gas turbine | |
GB1271819A (en) | Improvements in film cooling of structural members in gas turbine engines | |
GB1101543A (en) | Improvements in turbine diaphragm structure | |
SU358525A1 (en) | Coolable turbine blade | |
GB1075910A (en) | Improvements in or relating to blades for mounting in fluid flow ducts | |
GB1462470A (en) | Axial flow reaction turbine | |
GB1304678A (en) | ||
GB834811A (en) | Cooled hollow turbine blades | |
GB252702A (en) | Improvements in the reaction blading of steam and gas turbines | |
GB807181A (en) | Blade for gas turbine engines | |
GB1053420A (en) | ||
Came | Secondary loss measurements in a cascade of turbine blades | |
RU94045348A (en) | Cooled nozzle blade with vortex die | |
GB1366704A (en) | Hollow cool'd blade for a gas | |
US3384346A (en) | Aerofoil shaped blade for a fluid flow machine such as a gas turbine engine | |
US3427001A (en) | Aerofoil shaped blade | |
GB1268301A (en) | Improvements in or relating to gas turbine engines |