SU1204749A1 - Blade of axial flow turbomachine - Google Patents
Blade of axial flow turbomachine Download PDFInfo
- Publication number
- SU1204749A1 SU1204749A1 SU843764716A SU3764716A SU1204749A1 SU 1204749 A1 SU1204749 A1 SU 1204749A1 SU 843764716 A SU843764716 A SU 843764716A SU 3764716 A SU3764716 A SU 3764716A SU 1204749 A1 SU1204749 A1 SU 1204749A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- blade
- axial flow
- feather
- flow turbomachine
- shaped plate
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
г 1g 1
Изобретение относитс к турбомаши- ностроеншо и касаетс лопаток осевых вентил торов.This invention relates to turbomachine and relates to axial fan blades.
Цель изобретени - снижение трудоемкости изготовлени лопатки.The purpose of the invention is to reduce the labor intensity of manufacturing the blade.
На фиг. 1 изображена лопатка осевой турбомашины; на фиг. 2 - сечение А-А на фиг. 1.FIG. 1 shows a blade axial turbomachine; in fig. 2 is a section A-A in FIG. one.
Лопатка осевой турбо:1апшны содержит перо 1 с отверсти ми 2 по периферии и П-образную пластину 3, охватывающую периферийную часть пера 1, выполненную из материала, отличающегос от материала пера 1, и имеющуюPaddle axial turbo: 1 capsule contains a feather 1 with openings 2 on the periphery and a U-shaped plate 3, covering the peripheral part of the feather 1, made of a material different from the material of the feather 1, and having
047491047491
толщину bj меньшую, чем толщина Ъ пера 1. Одна из сторон П-образной пластины 3 снабжена выступами 4, расположенными в отверсти х 2 пера 1 5 и соединенными торцами 5 с противо- положной стороной пластины 3.the thickness bj is smaller than the thickness b of the pen 1. One of the sides of the U-shaped plate 3 is provided with protrusions 4 located in the openings 2 of the pen 1 5 and connected by the ends 5 with the opposite side of the plate 3.
При изготовлении лопатки П-образную пластину 3 устанавливают на пе- 10 риферийную часть пера 1, при этом выступы 4 вход т в отверсти 2, а затем торцы 5 выступов 4 соедин ют с противоположной стороной пластины 3, например, сваркой.When manufacturing the blade, the U-shaped plate 3 is mounted on the peripheral portion of pen 1, the protrusions 4 entering the holes 2, and then the ends 5 of the projections 4 are connected to the opposite side of the plate 3, for example, by welding.
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU843764716A SU1204749A1 (en) | 1984-07-04 | 1984-07-04 | Blade of axial flow turbomachine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU843764716A SU1204749A1 (en) | 1984-07-04 | 1984-07-04 | Blade of axial flow turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
SU1204749A1 true SU1204749A1 (en) | 1986-01-15 |
Family
ID=21128271
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU843764716A SU1204749A1 (en) | 1984-07-04 | 1984-07-04 | Blade of axial flow turbomachine |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU1204749A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2646168C2 (en) * | 2012-03-09 | 2018-03-01 | Снекма | Turbomachine blade containing overlay protecting the blade end |
RU2730201C2 (en) * | 2015-09-28 | 2020-08-19 | Сафран Эркрафт Энджинз | Blade, vane manufacturing method and turbojet engine containing such blade |
-
1984
- 1984-07-04 SU SU843764716A patent/SU1204749A1/en active
Non-Patent Citations (1)
Title |
---|
Авторское свидетельство СССР № 1116187, кл. F 01 D 5/20, 1983. * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2646168C2 (en) * | 2012-03-09 | 2018-03-01 | Снекма | Turbomachine blade containing overlay protecting the blade end |
RU2730201C2 (en) * | 2015-09-28 | 2020-08-19 | Сафран Эркрафт Энджинз | Blade, vane manufacturing method and turbojet engine containing such blade |
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