File:Jet engine numbered.svg

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Jet_engine_numbered.svg‎ (SVG file, nominally 910 × 380 pixels, file size: 447 KB)

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This file was a candidate in Picture of the Year 2008.

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Picture of the day This image was selected as a picture of the day for 2 April 2008(2008-04-02). It was captioned as follows:
English: Diagram of a typical gas turbine jet engine.
  Other languages

[edit] Summary

Inkscape logo 2.svg

This vector image was created with Inkscape.
Description
Deutsch: Schemazeichnung eines typischen Gasturbinen-Triebwerks. Luft wird durch die Gebläsesschaufeln im Verdichterabschnitt komprimiert, wenn sie in die Turbine eintritt. Sie wird mit Kraftstoff gemischt und im Verbrennungsabschnitt verbrannt. Die heißen Abgase entwickeln Schub nach vorne und drehen die Turbinenschaufeln und damit die Gebläseschaufeln im Verdichterabschnitt.
  1. Einlass
  2. Niederdruckkompressor (Fan)
  3. Hochdruckkompressor
  4. Verbrennung
  5. Turbine und Schubdüse
  6. Heißer Abschnitt
  7. Hoch- und Niederdruckturbine
  8. Brennkammern
  9. Kalter Abschnitt
  10. Lufteinlass
English: Diagram of a typical gas turbine jet engine. Air is compressed by the fan blades as it enters the engine, and it is mixed and burned with fuel in the combustion section. The hot exhaust gases provide forward thrust and turn the turbines which drive the compressor fan blades.
  1. Intake
  2. Low pressure compression
  3. High pressure compression
  4. Combustion
  5. Exhaust
  6. Hot section
  7. Turbines Low and High pressure
  8. Combustion chambers
  9. Cold section
  10. Air inlet
Français : Schéma montrant un turboréacteur d'avion typique (simple flux, simple corps). L'air est comprimé par les pales en entrant dans le réacteur, puis est mélangé avec le carburant qui brule dans la chambre de combustion. Les gaz d'échappement génèrent une forte réaction vers l'avant, et font également tourner les turbines qui actionnent les pales de compression.
  1. Admission de l'air
  2. Compression - basse pression
  3. Compression - haute pression
  4. Combustion
  5. Échappement
  6. Section chaude
  7. Turbines basse et haute pression
  8. Chambres de combustion
  9. Section froide
  10. Bouche d'entrée de l'air
Español: Esquema de un motor estándar a reacción. El aire es comprimido por las palas del ventilador, para ser mezclado con el carburante y explosionado en la cámara de compresión. La salida de los gases realiza un fuerte empuje hacia delante y hacen girar las turbinas que accionan las palas de compresión.
  1. Admisión
  2. Compresión - baja presión
  3. Compresión - alta presión
  4. Combustión
  5. Escape
  6. Sección caliente
  7. Turbina baja y alta presión
  8. Cámaras de combustión
  9. Sección fría
  10. Entrada de aire
Català: Esquema d'un motor estàndard a reacció. L'aire d'entrada es comprimit per les pales o àleps del ventilador, per ser seguidament barrejat amb el combustible a la cambra de combustió. La sortida dels gasos provoca l'impuls i fa girar les turbines, les quals mouen les pales de compressió.
  1. Admissió
  2. Compressió - baixa pressió
  3. Compressió - alta pressió
  4. Combustió
  5. Escapament
  6. Secció calenta
  7. Turbina baixa i alta pressió
  8. Cambres de combustió
  9. Secció freda
  10. Entrada d'aire
Română: Schema unei. Aerul indus este comprimat de paletele compresorului, după care intră în camera de ardere, unde este introdus combustibil. Amestecul este aprins, iar gazul obţinut se destinde în câteva turbine, efectuând lucru mecanic asupra lor. În imagine sunt specificate următoarele părţi componente:
  1. Zona de admisie
  2. Compresor de presiune joasă
  3. Compresor de presiune înaltă
  4. Ardere (combustie)
  5. Zona de evacuare
  6. Zona caldă
  7. Turbinele de presiune înaltă, medie şi, respectiv, joasă
  8. Camera de ardere (de combustie)
  9. Zona rece
  10. Admisia gazului (de obicei, aer).
Русский: Схема турбореактивного двигателя. Воздух сжимается лопастями компрессора, смешивается с топливом, смесь поступает в камеру сгорания. Горячие выхлопные газы обеспечивают движение вперёд и приводят в действие компрессор.
  1. Забор воздуха
  2. Компрессор низкого давления
  3. Компрессор высокого давления
  4. Камера сгорания
  5. Расширение рабочего тела в турбине и сопле
  6. Горячая зона
  7. Турбина
  8. Зона сгорания топлива
  9. Холодная зона
  10. Входное устройство
Polski: Schemat jednoprzepływowego silnika turboodrzutowego. Powietrze pod ciśnieniem wtłaczane jest przez sprężarkę do komory spalania gdzie dostarczane jest paliwo i zachodzi proces spalania. Gorące spaliny napędzają turbinę połączona wałem ze sprężarką.
  1. Dyfuzor wlotowy
  2. Sprężarka niskiego ciśnienia
  3. Sprężarka wysokiego ciśnienia
  4. Komory spalania
  5. Dysza wylotowa wraz z turbin
  6. Część gorąca
  7. Turbiny wysokiego i niskiego ciśnienia
  8. Rura ogniowa
  9. Część zimna
  10. Wlot powietrza
中文: 一个典型的燃气涡轮喷气发动机图解。
Date

07:09, 7 January 2008 (UTC)
Source

self-made, vector version of en:Image:FAA-8083-3A Fig 14-1.PNG which comes from an FAA handbook
Author

Jeff Dahl
Permission
(Reusing this image)		 See below.
Other versions

English version

French version

[edit] Licensing

I, the copyright holder of this work, hereby publish it under the following licenses:
GNU head Permission is granted to copy, distribute and/or modify this document under the terms of the GNU Free Documentation License, Version 1.2 or any later version published by the Free Software Foundation; with no Invariant Sections, no Front-Cover Texts, and no Back-Cover Texts. A copy of the license is included in the section entitled "GNU Free Documentation License".

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Creative Commons Attribution iconCreative Commons Share Alike icon		 This file is licensed under the Creative Commons Attribution ShareAlike 3.0, Attribution ShareAlike 2.5, Attribution ShareAlike 2.0 and Attribution ShareAlike 1.0 License. In short: you are free to share and make derivative works of the file under the conditions that you appropriately attribute it, and that you distribute it only under a license identical to this one. Official license.

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File history

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Date/TimeThumbnailDimensionsUserComment
current04:25, 8 January 2008Thumbnail for version as of 04:25, 8 January 2008910×380 (447 KB)Jeff Dahl (Talk | contribs) (Label fixes)
18:45, 7 January 2008Thumbnail for version as of 18:45, 7 January 2008910×380 (444 KB)Jeff Dahl (Talk | contribs) (stroke to path)
18:43, 7 January 2008Thumbnail for version as of 18:43, 7 January 2008910×380 (444 KB)Jeff Dahl (Talk | contribs) (Bracket fixes)
18:40, 7 January 2008Thumbnail for version as of 18:40, 7 January 2008910×380 (443 KB)Jeff Dahl (Talk | contribs) (Bracket fixes)
18:37, 7 January 2008Thumbnail for version as of 18:37, 7 January 2008910×380 (443 KB)Jeff Dahl (Talk | contribs) (bracket fixes)
18:32, 7 January 2008Thumbnail for version as of 18:32, 7 January 2008910×380 (443 KB)Jeff Dahl (Talk | contribs) (rm whitespace)
07:09, 7 January 2008Thumbnail for version as of 07:09, 7 January 20081,000×400 (444 KB)Jeff Dahl (Talk | contribs) ({{Inkscape}} {{Information |Description={{en|Diagram of a typical gas turbine jet engine.}} |Source=self-made |Date=~~~~~ |Author= Jeff Dahl |Permission= |other_versions=100px }} )

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