SU1677346A1 - Turbomachine blade - Google Patents

Turbomachine blade Download PDF

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Publication number
SU1677346A1
SU1677346A1 SU884372113A SU4372113A SU1677346A1 SU 1677346 A1 SU1677346 A1 SU 1677346A1 SU 884372113 A SU884372113 A SU 884372113A SU 4372113 A SU4372113 A SU 4372113A SU 1677346 A1 SU1677346 A1 SU 1677346A1
Authority
SU
USSR - Soviet Union
Prior art keywords
channels
channel
turbomachine blade
section
turbomachine
Prior art date
Application number
SU884372113A
Other languages
Russian (ru)
Inventor
Иван Иванович Кириллов
Виталий Юрьевич Тихоплав
Владимир Дмитриевич Сенюков
Геннадий Андреевич Шишов
Юрий Васильевич Петров
Original Assignee
Всесоюзный Проектно-Технологический Институт Энергетического Машиностроения
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 Всесоюзный Проектно-Технологический Институт Энергетического Машиностроения filed Critical Всесоюзный Проектно-Технологический Институт Энергетического Машиностроения
Priority to SU884372113A priority Critical patent/SU1677346A1/en
Application granted granted Critical
Publication of SU1677346A1 publication Critical patent/SU1677346A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Изобретение относитс  к турбомашино- строению и позвол ет повысить КПД. Это достигаетс  путем организации потока рабочего тела вдоль каналов 6, выполненных на поверхност х пера 1 в направлении от входной к выходной кромкам 4 и 5. В зонах этих кромо к поверхность каналов 6 плавно сопр жена с поверхност ми пера 1. Каждый канал 6 имеет поперечное сечение в форме сегмента и на поверхности канала 6 нанесен регул рный микрорельеф. 1 з.п. ф-лы, 3 ил,The invention relates to a turbomachine structure and allows an increase in efficiency. This is achieved by organizing the flow of the working medium along the channels 6, made on the surfaces of the pen 1 in the direction from the entrance to the exit edges 4 and 5. In the areas of these chromosc to the surface of the channels 6, the surfaces of the feather 1 are smoothly joined a section in the form of a segment and on the surface of the channel 6 a regular microrelief is applied. 1 hp f-ly, 3 silt,

Description

Изобретение относитс  к турбомашино- строению, в частности к лопатке турбома- шины.The invention relates to a turbomachine structure, in particular to a turbomachine blade.

Цель изобретени  - повышение КПД.The purpose of the invention is to increase efficiency.

На фиг.1 показана лопатка турбомаши- ны; на фиг.2 - сечение А-А на фиг. 1; на фиг.З - сечение Б-Б на фиг.1.Figure 1 shows a turbomachine blade; 2 is a section A-A in FIG. one; on fig.Z - section bb in figure 1.

Лопатка турбомашины содержит перо 1 с выполненными на ее поверхност х 2 и 3 в направлении от входной к выходной кромкам 4 и 5 каналами 6, которые могут быть ориентированы вдоль линии тока. Каждый канал 6 имеет поперечное сечение в форме сегмента с радиусом R. Поверхности 7 каналов 6 в зоне входной и выходной кромок 4 и 5 плавно сопр жены с поверхност ми 2 и 3 пера 1. На поверхности 7 каждого канала 6 может быть выполнен регул рный микрорельеф .The turbomachine blade contains a feather 1 with channels 6, which are made on its surfaces 2 and 3 in the direction from the entrance to the output edges 4 and 5, which can be oriented along the streamline. Each channel 6 has a cross section in the shape of a segment with a radius R. The surfaces 7 of the channels 6 in the zone of the input and output edges 4 and 5 smoothly mate with the surfaces 2 and 3 of the feathers 1. On the surface 7 of each channel 6 a regular microrelief .

Во врем  работы турбомашины поток рабочего тела движетс  по каналам 6, которые организуют этот поток вдоль линии тока . Регул рный микрорельеф снижает аэродинамическое сопротивление обтекание поверхности каналов 6.During operation of the turbomachine, the flow of working fluid moves along channels 6, which organize this flow along the streamline. A regular microrelief reduces aerodynamic drag on the surface of the channels 6.

Claims (2)

1.Лопатка турбомашины, содержаща  перо с выполненными на его поверхност х в направлении от входной к выходной кромкам каналами, отличающа с  тем, что, с целью повышени  КПД каждый канал имеет поперечное сечение в форме сегмента , а поверхности каналов в зоне входной и выходной кромок плавно сопр жены с поверхност ми пера.1. A turbomachine blade containing a feather with channels formed on its surfaces in the direction from the inlet to the outlet edges, characterized in that, in order to increase efficiency, each channel has a cross section in the shape of a segment, smoothly interfaced with the surface of the specimen. 2.Лопатка по п. 1,отличающа с  тем, что на поверхности каждого канала выполнен регул рный микрорельеф.2. A blade according to claim 1, characterized in that a regular microrelief is made on the surface of each channel. (Л(L СWITH о XI VJabout xi vj GJ 4 ОGj 4 o Фиг. 2FIG. 2 Фиг.ЗFig.Z
SU884372113A 1988-02-01 1988-02-01 Turbomachine blade SU1677346A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU884372113A SU1677346A1 (en) 1988-02-01 1988-02-01 Turbomachine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU884372113A SU1677346A1 (en) 1988-02-01 1988-02-01 Turbomachine blade

Publications (1)

Publication Number Publication Date
SU1677346A1 true SU1677346A1 (en) 1991-09-15

Family

ID=21353092

Family Applications (1)

Application Number Title Priority Date Filing Date
SU884372113A SU1677346A1 (en) 1988-02-01 1988-02-01 Turbomachine blade

Country Status (1)

Country Link
SU (1) SU1677346A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE9316009U1 (en) * 1993-10-20 1994-01-13 Moser, Josef, 85435 Erding Surface of a fluid-flowed body
DE4319628A1 (en) * 1993-06-15 1994-12-22 Klein Schanzlin & Becker Ag Structured surfaces of fluid machine components
EP2612991A3 (en) * 2012-01-03 2014-03-19 General Electric Company Gas turbine nozzle with a flow groove

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Патент US № 3575530, кл. 416-131, опублик.1971. *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4319628A1 (en) * 1993-06-15 1994-12-22 Klein Schanzlin & Becker Ag Structured surfaces of fluid machine components
DE9316009U1 (en) * 1993-10-20 1994-01-13 Moser, Josef, 85435 Erding Surface of a fluid-flowed body
US5860626A (en) * 1993-10-20 1999-01-19 Moser; Josef Surface of a body exposed to circumfluent fluid
EP2612991A3 (en) * 2012-01-03 2014-03-19 General Electric Company Gas turbine nozzle with a flow groove
US9062554B2 (en) 2012-01-03 2015-06-23 General Electric Company Gas turbine nozzle with a flow groove

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