TURBINE ENGINE COMPRISING SUSPENSION MEANS

The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure...

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Bibliographische Detailangaben
Hauptverfasser:	LECLERC BENOIT BERNARD RENE, GARNAUD QUENTIN MATTHIAS EMMANUEL, MOUTON HERVE JEAN ALBERT, GLEMAREC GUILLAUME, SEIZE GUILHEM
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and suspension means (12, 13) of the turbine engine (1), for attaching the turbine engine (1) on a pylon (11) of an aircraft. 本发明涉及一种沿着轴线(X)延伸的涡轮机(1)，所述涡轮机包括：高压主体，所述高压主体具有旋转地联接到高压涡轮(6)的高压压缩机(4)，以及低压主体，所述低压主体包含旋转地联接到低压涡轮(7)的低压压缩机(3)；上游壳体(14)，所述上游壳体位于所述高压压缩机(4)的上游；以及所述涡轮机(1)的悬架构件(12、13)，其预期用于将所述涡轮机(1)附接到飞机吊架(11)。