Bypass turbojet

Patent metadata

Field	Value
Publication number	US-9611865-B2
Application number	US-201213978047-A
Country	US
Kind code	B2
Filing date	Jan 5, 2012
Priority date	Jan 11, 2011
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

A bypass turbojet including a fan wheel carrying blades and surrounded by an annular casing, the casing including an air suction mechanism sucking air from an annular clearance formed between the casing and radially outer ends of the blades of the fan wheel. The air suction mechanism includes an inlet including at least one inlet slot formed in an inside wall of the casing and connected to a suction channel extending downstream. The inlet slot of the suction mechanism is situated axially in register solely with upstream portions of chords of the blades of the fan wheel at their radially outer ends.

First claim

The invention claimed is:

1. A bypass turbojet comprising:
a fan wheel carrying blades and surrounded by an annular casing,
the casing including air suction means for sucking air from an annular clearance formed between the casing and radially outer ends of the blades of the fan wheel,
the suction means comprising an inlet including at least one inlet slot formed in an inside wall of the casing and connected to a suction channel extending downstream,
wherein the blades of the fan wheel are upstream of a primary passage for a primary stream in which a low-pressure compressor and a high-pressure compressor are disposed, and a secondary passage for a secondary stream in which outlet guide vanes are disposed,
wherein the inlet slot of the suction means is situated axially in register only with upstream portions of chords of the blades of the fan wheel at radially outer ends thereof so as to face the radially outer ends of the upstream portions of the chords of the blades of the fan wheel in a radial direction,
wherein an outlet of the suction channel is provided in the annular casing axially downstream of the outlet guide vanes, and
wherein the suction means comprises a suction pump housed in the casing.

2. A turbojet according to claim 1 , wherein the inlet slot has an axial dimension in a range of 3% to 10% of the chord of the blades at the radially outer ends thereof.

3. A turbojet according to claim 1 , wherein the inlet slot is annular or includes a plurality of orifices distributed around an axis of the fan.

4. A turbojet according to claim 1 , wherein the suction means comprises at least two inlet slots formed in the inside wall of the casing and axially offset relative to each other.

5. A turbojet according to claim 1 , wherein the air suction means comprises an annular manifold housed in the casing and connected to the inlet slot via suction channels.

6. A turbojet according to claim 1 , wherein the outlet of the suction channel is provided in an outside wall or in the inside wall of the casing.

7. A turbojet according to claim 6 , wherein the outlet of the suction channel is provided in the inside wall of the casing.

8. A turbojet according to claim 1 , wherein 0.5% to 2% of a total air flow passing through the fan wheel is taken by the at least one inlet slot.

Assignees

• Morel Cedric
• Vuillemin Alexandre Alfred Gaston
• Snecma

Inventors

• Morel Cedric
• Vuillemin Alexandre Alfred Gaston

Classifications

• F04D29/663 Primary

  Sound attenuation · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F04D29/682

  by fluid extraction · CPC title

• F02K3/06

  with front fan · CPC title

• F02C7/045

  having provisions for noise suppression · CPC title