Turbine engine fan module including a turbine engine inlet cone de-icing system, and a de-icing method

Patent metadata

Field	Value
Publication number	US-10760486-B2
Application number	US-201615561116-A
Country	US
Kind code	B2
Filing date	Mar 31, 2016
Priority date	Mar 31, 2015
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

The invention relates to an aviation turbine engine fan module including a de-icing system ( 10 ) for de-icing an inlet cone ( 1 ) and comprising a sheath ( 30 ) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct ( 38 ) having at least one hot air admission orifice ( 42 ), said first duct being configured to convey hot air from a bearing enclosure ( 22 ) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct ( 40 ) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.

First claim

The invention claimed is:

1. An aviation turbine engine fan module including an inlet cone, a lubrication bearing enclosure, and a de-icing system for de-icing the inlet cone, said de-icing system comprising a sheath placed within a space defined in the inlet cone, said sheath comprising a first duct having at least one hot air admission orifice, said first duct being configured to convey hot air from the lubrication bearing enclosure towards a wall of the inlet cone in order to heat the inlet cone from an inside of the inlet cone,
wherein the sheath further comprises a second duct having at least one outlet situated downstream from the at least one hot air admission orifice of the first duct, said second duct being configured to discharge the hot air from the first duct towards a downstream end of an engine,
wherein the aviation turbine engine fan module further includes a fan drive shaft defining a downstream end of the space, and
wherein the de-icing system further includes a sealing collar positioned on an outer surface of the sheath and bearing against the fan drive shaft, the sealing collar serving to hold the sheath in leaktight manner within the fan drive shaft, the sealing collar extends radially outward from the outer surface of the sheath, and wherein the outer surface of the sheath extends substantially parallel to the fan drive shaft.

2. The aviation turbine engine fan module according to claim 1 , wherein the sheath comprises:
an inner tube centered on a longitudinal axis of the engine; and
an outer tube arranged coaxially around the inner tube, the first duct being defined radially between the inner tube and the outer tube and being closed at a downstream end by an annular plate extending radially between the inner tube and the outer tube, the second duct being defined by an inside of the inner tube.

3. The aviation turbine engine fan module according to claim 1 , further comprising at least one de-oiling system between the lubrication bearing enclosure and the first duct.

4. The aviation turbine engine fan module according to claim 3 , wherein the de-oiling system comprises at least one chimney mounted in leaktight manner at one end on the outer tube facing an admission orifice of the first duct so as to open out therein, said chimney being for opening out at another end inside the lubrication bearing enclosure.

5. The aviation turbine engine fan module according to claim 2 , wherein the inner tube and the outer tube are each of circular cross-section and of diameter that increases from upstream to downstream.

6. The aviation turbine engine fan module according to claim 2 , wherein the outer tube is fastened in leaktight manner to the inlet cone by a flange situated at an upstream end of said outer tube.

7. A de-icing method for de-icing an aviation turbine engine inlet cone, the de-icing method comprising using a first duct of a sheath placed within a space defined in the aviation turbine engine inlet cone, said first duct having at least one hot air admission orifice that conveys hot air taken from an inside of a bearing enclosure to a wall of the aviation turbine engine inlet cone of an engine in order to heat said aviation turbine engine inlet cone from an inside of the aviation turbine engine inlet cone, the de-icing method being characterized in that the de-icing method further comprises discharging the hot air from the first duct via a second duct of the sheath from the aviation turbine engine inlet cone towards a downstream end of the engine, the hot air being discharged from upstream to downstream by flowing inside at least one rotor shaft of the engine, the at least one rotor shaft of the engine being coupled to a fan drive shaft, wherein a sealing collar positioned on an outer surface of the sheath and bearing against the fan drive shaft, holds the sheath in leaktight manner within the fan drive shaft, the sealing collar extends radially outward from the outer surface of the sheath, and wherein the outer surface of the sheath extends substantially parallel to the fan drive shaft.

8. The de-icing method according to claim 7 , further comprising de-oiling the hot air taken from the inside of the bearing enclosure.

9. The de-icing method according to claim 7 , wherein the hot air discharged by the second duct is used to cool at least one member of the engine.

10. The aviation turbine engine fan module according to claim 2 , further comprising at least one de-oiling system between the lubrication bearing enclosure and the first duct.

Assignees

• Safran Aircraft Engines

Inventors

• Lemarchand Kevin Morgane
• Bordoni Nils
• Kubiak Guillaume

Classifications

• F05D2260/608

  Aeration, ventilation, dehumidification or moisture removal of closed spaces · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• F05D2260/609

  Deoiling or demisting · CPC title