INLET CONE FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED AIRCRAFT TURBINE ENGINE

The present invention concerns an inlet cone (10) for an aircraft turbine engine (1), comprising a frustoconical body (12) and a tip (11) made from elastically deformable material attached to an end (12p) of smaller diameter of the body (12), the tip (11) comprising an apex configured to be situated...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	BATONNET BAPTISTE, LOUIS ALBAN
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	The present invention concerns an inlet cone (10) for an aircraft turbine engine (1), comprising a frustoconical body (12) and a tip (11) made from elastically deformable material attached to an end (12p) of smaller diameter of the body (12), the tip (11) comprising an apex configured to be situated on an axis of rotation (X) of the cone and an attachment base (11p) for attachment to the end (12p). According to the invention, the base (11p) has a generally circular or oval shape, this base extending in a connecting plane (P), and the connecting plane (P) is inclined relative to a transverse plane (T) perpendicular to the axis of rotation (X). The present invention further concerns an aircraft turbine engine (1), comprising such an inlet cone (10). 本发明涉及一种用于飞行器涡轮发动机(1)的入口锥体(10)，所述入口锥体包括截头圆锥主体(12)和尖端(11)，尖端由附接到主体(12)的较小直径的端部(12p)的能弹性变形的材料制成，尖端(11)包括顶部和附接基座(11p)，顶部被构造为位于锥体的旋转轴线(X)上，附接基座用于附接到端部(12p)。根据本发明，基座(11p)通常呈圆形或椭圆形，该基座在连接平面(P)中延伸，并且连接平面(P)相对于与所述旋转轴线(X)垂直的横向平面(T)倾斜。本发明进一步涉及一种飞行器涡轮发动机，该飞行器涡轮发动机包括这种入口锥体(10)。