SU985327A1 - Axial-flow turbomachine impeller - Google Patents

Axial-flow turbomachine impeller Download PDF

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Publication number
SU985327A1
SU985327A1 SU802893813A SU2893813A SU985327A1 SU 985327 A1 SU985327 A1 SU 985327A1 SU 802893813 A SU802893813 A SU 802893813A SU 2893813 A SU2893813 A SU 2893813A SU 985327 A1 SU985327 A1 SU 985327A1
Authority
SU
USSR - Soviet Union
Prior art keywords
blades
grooves
disk
side walls
wheel
Prior art date
Application number
SU802893813A
Other languages
Russian (ru)
Inventor
Леонид Павлович Батвинов
Валерий Иванович Герман
Юрий Борисович Зайцев
Original Assignee
Всесоюзное Научно-Производственное Объединение "Союзтурбогаз"
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 Всесоюзное Научно-Производственное Объединение "Союзтурбогаз" filed Critical Всесоюзное Научно-Производственное Объединение "Союзтурбогаз"
Priority to SU802893813A priority Critical patent/SU985327A1/en
Application granted granted Critical
Publication of SU985327A1 publication Critical patent/SU985327A1/en

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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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Landscapes

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

Description

(5) РАБОЧЕЕ КОЛЕСО ОСЕВОЙ ТУРБОМАШИНЫ(5) WORKING WHEEL AXIAL TURBO MILL

1one

Изобретение относитс  к турбомашиностроению . .This invention relates to turbomachinery. .

Наиболее близким к предлагаемому  вл етс  рабочее колесо осевой турбомашины , содержащее двухъ русные лопатки , с бандажными полками и хвостовиками , расположенными в пазах диска и контактирующими с боковыми стенками последних Л .Closest to the present invention, there is an impeller of an axial turbomachine containing two-bladed blades, with retaining shelves and liners located in the disc grooves and in contact with the side walls of the latter L.

Недостатком указанного устройства  вл етс  сложность сборки ступени и недоЬтаточна  надежность. The disadvantage of this device is the difficulty of assembling the stage and the lack of reliability.

Цель изобретени  - упрощение сборки .The purpose of the invention is to simplify the assembly.

Указанна  цель достигаетс  тем, что обращенные одна к другой поверхности бандажных полок выполнены эквидистантно контактирующим поверхност м хвостовиков лопаток и боковых стенок пазов диска.This goal is achieved by the fact that the surfaces of the retaining shelves facing one another are made equidistantly in contact with the surfaces of the shanks of the blades and the side walls of the disk grooves.

Кроме того, контактирующие поверхности хвостовиков лопаток и боковых стенок пазов диска выполнены наклонНО к оси колеса. А также контактирующие поверхности хвостовиков лопдток и боковых стенок пазов диска выполнены по дугам окружности.In addition, the contacting surfaces of the shanks of the blades and the side walls of the disc grooves are inclined to the wheel axis. As well as the contacting surfaces of the shank lobes and the side walls of the disc grooves are made along circular arcs.

На фиг. t изображено колесо осевой турбомашины, продольньм разрез; на фиг. 2 - сечение А-А на фиг. 1; на фиг. 3 вид в аксонометрии , вариант выполнени  рабочего колеса; на фиг. - вид по стрелке Б FIG. t shows the axial turbomachine wheel, longitudinal section; in fig. 2 is a section A-A in FIG. one; in fig. 3 is a perspective view of an embodiment of the impeller; in fig. - view along arrow B

10 на фиг. 3.10 in FIG. 3

Рабочее колесо осевой турбомашины содержит двухъ русные лопатки 1 с бандажными полками 2 и хвостовиками The impeller of the axial turbomachine contains two-blond blades 1 with retaining shelves 2 and shanks

Claims (3)

ts 3, которые расположейы в пазах диска k и контактируют с (Зоковыми стенками последних. Причем обращенные друг к другу поверхности 5 и 6 и ба(:1дажных .полок 2 выполнены эквидистантно кон20 тактирующим поверхност м 7 хвостовиков 3 лопаток 1 и боковых стенок па ,зов диска . Контактирующие поверхности 7 хвостовиков 3 лопаток 1 и бо9 ковых стенок пазов диска выполнены наклонно к оси колеса (фиг. 1 и Кроме того, контактирующие повер ности 7 хвостовиков 3 лопаток 1 и боковых стенок пазов диска могут быть выполнены по дугам окружности (фиг. 3 и ). При сборке рабочего ко леса турбомашины лопатки Т хвостовиками 3 закрепл ют на приспособлении (не показано). Затем лопатки 1 устанавливают в пазы диска Ц, при этом вследствие эквидистантности обращенных друг к другу поверхностей 5 и 6 бандажных полок 2 контактирующим поверхност м 7 хвостовиков 3 лопаток 1 и боковым стенкам пазов диска k одновременно полки 2 соседних лопаток 1 колеса вход т в контакт. -.. Предлагаемое рабочее колесо позво л ет упростить техно югию сборки .,..... ЛГ... бочего колеса турбомашины, увеличить прочность замкового соединени  и повысить надежность. Формула изобретени  1. Рабочее колесо осевой турбомашины , содержащее двухъ русные лопат7 ки с бандажными полками и хвостови- . ками, расположенными в пазах диска и контактирующими с боковыми стенками последних, отличающеес  тем, что, с целью упрощени  сборки, обращенные одна к другой поверхности бандажных полок выполнены эквидистантно контактирующим поверхност м хвостовиков лопаток и боковых стенок пазов диска. ts 3, which are located in the grooves of the disk k and are in contact with (the lateral walls of the latter. Moreover, surfaces 5 and 6 and ba facing each other (: 1 of the equal 2) are made equidistantly matching the timing surfaces of 7 of the shanks of 3 blades 1 and side walls na, disc call. The contacting surfaces 7 of the shanks 3 of the vanes 1 and the side walls of the disk grooves are inclined to the wheel axis (Fig. 1 and In addition, 7 surfaces of the blades 3 of the blades 1 and the side walls of the disk grooves in contact can be made along circular arcs (Fig 3 and). When assembling p The scoop of the turbomachine blade T is secured to the shanks 3 by a device (not shown). The blades 1 are then installed into the slots of the disk C, and due to the equidistance of the facing surfaces 5 and 6 of the retaining shelves 2 to the contacting surfaces 7 of the tails 3 of the blades 1 and the sidewalls of the grooves of the disk k at the same time the shelves of 2 adjacent blades 1 of the wheel come into contact. The proposed impeller makes it possible to simplify the assembly technology., ..... LH ... of the boom wheel of the turbomachine, increase the strength of the locking connection raise reliability Claims 1. An impeller for an axial turbomachine containing two double-bladed 7 blades with retaining shelves and tails. Kami located in the grooves of the disk and in contact with the side walls of the latter, characterized in that, in order to simplify the assembly, facing one another to the surface of the retaining shelves are made equidistantly contacting the surfaces of the blades of the blades and the side walls of the grooves of the disk. 2.Коле со по п. 1, отличающеес  тем, что, контактирующие поверхности хвостовиков лопаток и боковых стенок пазов диска выполнены Наклонно к оси колеса. 2. Kole according to claim 1, characterized in that the contacting surfaces of the shanks of the blades and the side walls of the disc grooves are inclined to the axis of the wheel. 3.Колесо по п. 1, отличающеес  тем, что контактирующие -ч - V- V, л 1СП, MIU ионтактир поверхности хвостовиков лопаток %rf««VJ«V l боковых стенок пазов диска выполнены по дугам окружности. Источники информации, прин тые во внимание при .экспертизе К Авторское свидетельство СССР № 232986, кл.Р 01 D 5/U, 1967.3. A wheel according to claim 1, characterized in that the contacting -h -V-V, l 1SP, MIU iontaktir blade root surfaces% rf "" VJ "V l side walls of the grooves of the disk are made along circular arcs. Sources of information taken into account in expert examination K Copyright Certificate of the USSR No. 232986, cl. R 01 D 5 / U, 1967. А -АA-A фие.гfie.g
SU802893813A 1980-03-24 1980-03-24 Axial-flow turbomachine impeller SU985327A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU802893813A SU985327A1 (en) 1980-03-24 1980-03-24 Axial-flow turbomachine impeller

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU802893813A SU985327A1 (en) 1980-03-24 1980-03-24 Axial-flow turbomachine impeller

Publications (1)

Publication Number Publication Date
SU985327A1 true SU985327A1 (en) 1982-12-30

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4714410A (en) * 1986-08-18 1987-12-22 Westinghouse Electric Corp. Trailing edge support for control stage steam turbine blade
US4840539A (en) * 1987-03-12 1989-06-20 Alsthom Moving blading for steam turbines
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4714410A (en) * 1986-08-18 1987-12-22 Westinghouse Electric Corp. Trailing edge support for control stage steam turbine blade
US4840539A (en) * 1987-03-12 1989-06-20 Alsthom Moving blading for steam turbines
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine

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