FIELD: engines and pumps.
SUBSTANCE: mid housing (20) of turbojet blower compartment (Cs) comprises the following components: Shell ring (22), circular web (24), suspension beam (28) and auxiliary gearbox (30). Shell ring (22) is centred in gas turbine engine lengthwise axis (X-X). Circular web (24) is centred in engine lengthwise axis and located opposite shell ring downstream side. Suspension beam (28) is secured to said web to extend in flow direction, parallel with engine lengthwise axis. AGB (30) swivels on said beam and comprises upstream lateral side (30b) axially spaced from the web, downstream lateral side (30a) opposite said upstream lateral side. Besides, it comprises multiple auxiliary hardware (32) arranged opposite downstream lateral side and along engine lengthwise axis.
EFFECT: possibility to fit AGB in aircraft central compartment.
8 cl, 2 dwg
| Title |
Year |
Author |
Number |
| GAS TURBINE ENGINE CONTAINING SUSPENSION MEANS |
2019 |
- Garnaud, Quentin, Matthias, Emmanuel
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|
RU2784242C2 |
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2015 |
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|
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| IMPROVED FIRE-FIGHTING DEVICE INTENDED TO BE INSTALLED BETWEEN THE END OF THE AIRCRAFT GAS TURBINE ENGINE BACK PROP AND THE GAS TURBINE ENGINE HOOD LIMITING THE INTERMEDIATE FLOW COMPARTMENT |
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|
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2010 |
- Maksimov Nikolaj Ivanovich
|
RU2457153C2 |
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2015 |
- Lemarchand, Kevin, Morgane
|
RU2673027C2 |
| EXTERNAL COVER OF AIR PIPE OF GAS-TURBINE ENGINE FAN |
2008 |
- Derene Zhaki Rafaehl' Mishel'
- Dizhu Dehl'Fin Ehdit
- Regar Sebast'En
|
RU2462601C2 |
| SEALED FRONT CHAMBER DURING MODULAR DISMANTLING OF TURBOJET WITH REDUCTION GEAR |
2014 |
- Bro Mishel Zhilber Rolan
- Novakovski Natali
|
RU2674837C1 |
| BYPASS TURBOJET ENGINE AND INTERMEDIATE HOUSING THEREOF |
2011 |
|
RU2587029C2 |
| LIGHT MULTI-PURPOSE AIRCRAFT |
2002 |
- Efanov A.G.
- Demchenko O.F.
- Matveev A.I.
- Popovich K.F.
- Shkolin V.P.
- Naryshkin V.Ju.
- Kodola V.G.
|
RU2210522C1 |
| AIRCRAFT POWER PLANT |
2016 |
- Ezrokhi Yurij Aleksandrovich
- Kalenskij Sergej Miroslavovich
- Morzeeva Tatyana Andreevna
|
RU2644721C2 |
