IP Library Granted Patent US 8,322,125
Granted Patent B2
US 8,322,125 · App. 12/481,942 · Granted Dec 4, 2012

Turbo-engine compressor tip comprising de-icing means

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Quick Facts
Patent No.
US 8,322,125
App. No.
12/481,942
Granted
Dec 4, 2012
Kind
B2
Abstract

The de-icing system comprises a flexible bladder ( 5 ) filled with de-icing fluid, pressed by the centrifugal forces produced when the rotor tip ( 1 ) is rotating against the inner wall thereof to apply a pressure favoring the progressive and calibrated discharge of the fluid, in the absence of a pump and any other active means. For this, the bladder comprises a concavity ( 11 ) at the rear which is automatically enlarged under the effect of centrifugal forces during operation and discharges the fluid continuously from the bladder.

Claims (8)

1. Turbo-engine compressor tip directed toward a front direction, containing a de-icing fluid container, characterized in that the container is formed by a flexible bladder which comprises a concavity directed toward a rear direction, opposite the front direction and in that the container is provided with a filling valve, and at least one calibrated opening de-icing fluid distribution orifice.

2. Turbo-engine compressor tip according to claim 1 , characterized in that the distribution orifice is placed in the front direction with respect to the container and provided with an adjustable check valve.

3. Turbo-engine compressor tip according to claim 2 , characterized in that the check valve has an opening performed according to the temperature.

4. Turbo-engine compressor tip according to claim 3 , characterized in that the check valve comprises an active member made of shape memory alloy.

5. Turbo-engine compressor tip according to claim 3 , characterized in that the filling valve is located extending from the check valve.

6. Turbo-engine compressor tip according to claim 1 , characterized in that the container comprises a perforated peripheral face facing a spongy wall of the tip.

7. Turbo-engine compressor tip according to claim 1 , characterized in that the distribution orifice opens into a gap between two skins of a wall of the tip, including one outer skin permeable to the fluid.

8. Turbo-engine compressor tip according to claim 1 , characterized in that the bladder is made of fiber-reinforced polymer.

Assignments (3)
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 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jun 11, 2009
From: MONS, CLAUDE MARCEL; VERNET, MICHEL PAUL LUCIEN
To: SNECMA
Reel/Frame 022810/0251 →