IP Library Granted Patent US 8,585,352
Granted Patent B2
US 8,585,352 · App. 12/967,849 · Granted Nov 19, 2013

Turbojet nacelle

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Quick Facts
Patent No.
US 8,585,352
App. No.
12/967,849
Granted
Nov 19, 2013
Kind
B2
Abstract

The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Claims (11)

1. A nacelle for a bypass turbojet, the nacelle comprising:

an aerodynamic fairing;

a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; and

a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch;

wherein the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

2. A nacelle according to claim 1 , wherein the access hatch in the outer shroud is fastened to the maintenance cover by means of at least one connecting rod.

3. A nacelle according to claim 2 , wherein each connecting rod is fastened to the access hatch of the outer shroud and to the maintenance cover by means of ball joints.

4. A nacelle according to claim 2 , wherein each connecting rod is spring-mounted.

5. A nacelle according to claim 1 , further including sealing means between the access hatch of the outer shroud and the opening formed in the outer shroud.

6. A nacelle according to claim 1 , further including centering means for centering the access hatch of the outer shroud relative to the opening formed in the outer shroud.

7. An airplane bypass turbojet including a nacelle according to claim 1 .

Assignments (2)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →