Nozzle for an aircraft turboprop engine with an unducted fan

Patent metadata

Field	Value
Publication number	US-10113506-B2
Application number	US-201514881886-A
Country	US
Kind code	B2
Filing date	Oct 13, 2015
Priority date	Apr 15, 2013
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

First claim

What is claimed is:

1. A nozzle for an aircraft turboprop engine with an unducted fan, comprising:
an inner wall,
an outer wall being radially spaced apart from the inner wall and concentric with the inner wall,
a junction area of the inner and outer walls, the junction area comprising a plurality of first pads secured to the inner wall, and a plurality of second pads secured to the outer wall and facing the plurality of first pads,
wherein the plurality of first and second pads are positioned such that the plurality of first pads and the plurality of second pads are not in contact with each other to define a plurality of gaps therebetween when the turboprop engine is at a standstill and such that the plurality of second pads move toward the plurality of first pads to close the gaps to create bearing plane connections therebetween when the turboprop engine is in operation, the junction area being disposed at a trailing edge of the nozzle and comprising at least one opening to create ventilation between the inner and outer walls, the inner and outer walls being inclined toward each other at the junction area.

2. The nozzle according to claim 1 , wherein each of the inner and outer walls of the nozzle comprises at least one metallic skin made of an austenite nickel-chromium based superalloy.

3. The nozzle according to claim 1 , wherein the bearing plane connections are distributed discretely along a circumference of the nozzle, between the inner and outer walls of the nozzle.

4. The nozzle according to claim 1 , wherein the inner wall of the nozzle comprises a metallic skin made of an austenite nickel-chromium based superalloy, and the outer wall of the nozzle comprises a skin made of titanium.

5. The nozzle according to claim 1 , further comprising abutments disposed between the plurality of first and second pads.

6. The nozzle according to claim 1 , wherein the inner wall comprises at least a one annular stiffener positioned facing at least one annular stiffener of the outer wall.

7. The nozzle according to claim 1 , wherein the junction area of the inner and outer walls is located at a downstream section of the nozzle.

8. The nozzle according to claim 1 , wherein the inner and outer walls include connecting plates at the junction area for connecting the inner and outer walls, the junction area including a plurality of openings separated by the connecting plates.

9. A turboprop engine within an unducted fan, comprising:
a nozzle disposed downstream from the unducted fan, the nozzle comprising:
an inner wall;
an outer wall being radially spaced apart from the inner wall and concentric with the inner wall; and
a junction area of the inner and outer walls, the junction area comprising a plurality of first pads secured to the inner wall, and a plurality of second pads secured to the outer wall and facing the plurality of first pads,
wherein the plurality of first and second pads are positioned such that the plurality of first pads and the plurality of second pads are not in contact with each other to define a plurality of gaps therebetween when the turboprop engine is at a standstill and such that the plurality of second pads move toward the plurality of first pads to close the gaps to create bearing plane connections therebetween when the turboprop engine is in operation, the junction area being disposed at a trailing edge of the nozzle and comprising at least one opening to create ventilation between the inner and outer walls.

Assignees

• Aircelle Sa

Inventors

• Malot Hélène
• Guegou Jean-Pierre
• Bienvenu Philippe
• Prunin Philippe

Classifications

• F02K3/06

  with front fan · CPC title

• F02K1/822 Primary

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title