Turbomachine comprising a trap for foreign objects circulating in an air flow

Patent metadata

Field	Value
Publication number	US-10946975-B2
Application number	US-201615778954-A
Country	US
Kind code	B2
Filing date	Nov 25, 2016
Priority date	Nov 27, 2015
Publication date	Mar 16, 2021
Grant date	Mar 16, 2021

Abstract

A turbomachine of the «open rotor» type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.

First claim

The invention claimed is:

1. A turbomachine for an aircraft, said turbomachine comprising at least one unenclosed propeller and a nacelle defining an air inlet, a central hub positioned downstream of the air inlet and an air intake section surrounding the central hub and opening into an air supply main section, with the central hub comprising a central trap having an aperture for trapping foreign objects contained in an air flow entering the turbomachine, and the air intake section being totally annular about the aperture of the central trap, with the central trap comprising an air recovery channel configured as an annular air recovery channel, with said air recovery channel including a filter for filtering the foreign objects in recovered air, characterized in that one discharge end of said air recovery channel, through which said air recovery channel opens into the air supply main section, is provided on the central hub.

2. The turbomachine according to claim 1 , wherein the air inlet has an inner diameter having a first extremum, the central hub has an outer diameter having a second extremum, and the air supply main section has an outer diameter having a third extremum, with the second extremum being outside of a parallelogram formed by the first extremum, the third extremum, and an axis of symmetry of the turbomachine, in a plane radial to the axis of symmetry.

3. The turbomachine according to claim 1 , wherein the filter of the air recovery channel is positioned at an inlet of the air recovery channel, as an extension of an inner bottom wall of the central trap, so as to filter air circulating from the central trap to the air supply main section.

4. The turbomachine according to claim 1 , wherein the filter comprises a mesh for retaining the foreign objects contained in the air flow passing through said mesh.

5. The turbomachine according to claim 1 , wherein the central hub is centered on an axis and has an inner wall, which defines a limit of the aperture of the central trap, and an outer wall, and, radially to said axis, the aperture of the central trap extends between said axis and said inner wall.

6. The turbomachine according to claim 5 , wherein the central trap comprises an accommodation wherein the foreign objects are retained.

7. The turbomachine according to claim 5 , having a longitudinal axis and wherein the axis on which the central hub is centered is the longitudinal axis.

8. A turbomachine for an aircraft, said turbomachine comprising at least one unenclosed propeller and a nacelle defining an air inlet, a central hub positioned downstream of the air inlet and an air intake section surrounding the central hub and opening into an air supply main section, with the central hub comprising a central trap having an aperture for trapping foreign objects contained in an air flow entering the turbomachine, and the air intake section being totally annular about the aperture of the central trap, with the central trap comprising an air recovery channel comprising a tubular air recovery channel, with said air recovery channel including a filter for filtering the foreign objects in recovered air, characterized in that a discharge end of said air recovery channel, through which said air recovery channel opens into the air supply main section, is provided on the central hub.

9. The turbomachine according to claim 8 , wherein the tubular air recovery channel comprises a first tubular air recovery channel, and wherein the central trap comprises a second tubular air recovery channel including a second filter, with the first tubular air recovery channel being diametrically opposed to the second filter of the second tubular air recovery channel.

10. The turbomachine according to claim 8 , wherein the air inlet has an inner diameter having a first extremum, the central hub has an outer diameter having a second extremum, and the air supply main section has an outer diameter having a third extremum, with the second extremum being outside of a parallelogram formed by the first extremum, the third extremum, and an axis of symmetry of the turbomachine, in a plane radial to the axis of symmetry.

11. The turbomachine according to claim 8 , wherein the filter of the air recovery channel is positioned at an inlet of the air recovery channel, as an extension of an inner bottom wall of the central trap, so as to filter air circulating from the central trap to the air supply main section.

12. The turbomachine according to claim 8 , wherein the filter comprises a mesh for retaining the foreign objects contained in the air flow passing through said mesh.

13. The turbomachine according to claim 8 , wherein the central hub is centered on an axis and has an inner wall, which defines a limit of the aperture of the central trap, and an outer wall, and, radially to said axis, the aperture of the central trap extends between said axis and said inner wall.

14. The turbomachine according to claim 13 , wherein the central trap comprises a convex cavity into which the aperture opens downwardly and wherein the foreign objects are retained.

15. The turbomachine according to claim 13 , having a longitudinal axis and wherein the axis on which the central hub is centered is the longitudinal axis.

Assignees

• Safran Aircraft Engines

Inventors

• Ferrier Romain Jean-Claude
• Brogna Romeo
• Prouteau Jackie Raymond Julien
• Sirvin Nicolas Joseph

Classifications

• B64D33/02 Primary

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• Y02T50/60

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• F05D2260/607

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• F05D2220/325

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