SU358525A1 - Coolable turbine blade - Google Patents

Coolable turbine blade

Info

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
Application number
SU1496390A
Other languages
Russian (ru)
Inventor
Г. К. Андронов С. В. Гуров А. А. Канцепольский С. Копелев М. В. Авилова Шульгина
Original Assignee
Avilova Shulgina M V
Andropov G K
Gurov S V
Kanzepolski A A
Kopelev S Z
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 Avilova Shulgina M V, Andropov G K, Gurov S V, Kanzepolski A A, Kopelev S Z filed Critical Avilova Shulgina M V
Priority to SU1496390A priority Critical patent/SU358525A1/en
Application granted granted Critical
Publication of SU358525A1 publication Critical patent/SU358525A1/en

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.

SU1496390A 1970-12-09 1970-12-09 Coolable turbine blade SU358525A1 (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (7)

* Cited by examiner, † Cited by third party
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