Aeronautical thruster

Patent metadata

Field	Value
Publication number	US-12371152-B2
Application number	US-202218577064-A
Country	US
Kind code	B2
Filing date	Jul 4, 2022
Priority date	Jul 6, 2021
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

An aeronautical thruster having a longitudinal axis and having a hub and at least two annular rows of unducted blades including an upstream annular row and a downstream annular row which are spaced apart from one another along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, and the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade.

First claim

The invention claimed is:

1. An aeronautical thruster having a longitudinal axis, comprising:
a hub; and
at least two annular rows of unducted blades having an upstream annular row and a downstream annular row which are spaced apart from each other along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade,
wherein each blade of the upstream annular row has a radially outer radius, and wherein a relative difference in the radially outer radius of any among the first blade and the second blade of the downstream annular row in comparison to the radially outer radius of any of the blades of the upstream annular row is between −15% and 30%.

2. The aeronautical thruster according to claim 1 , wherein the downstream annular row is fixed around the longitudinal axis.

3. The aeronautical thruster according to claim 1 , wherein the first blade and the second blade of the downstream annular row each have a radially outer radius defined by the radially outer end of the corresponding blade, the radially outer radius of the first blade being greater than the radially outer radius of the second blade.

4. The aeronautical thruster according to claim 1 , wherein the first blade and the second blade of the downstream annular row are circumferentially consecutive.

5. The aeronautical thruster according to claim 1 , wherein each blade of the upstream annular row extends in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, the radial dimension of each of the blades of the upstream annular row being greater than the radial dimension of the first blade of the downstream annular row.

6. The aeronautical thruster according to claim 1 , wherein the radially outer ends of the blades of the downstream annular row are inscribed within an outer envelope whose projection onto a plane normal to the longitudinal axis defines a circle.

7. The aeronautical thruster according to claim 6 , wherein the center of the circle is offset relative to the longitudinal axis.

8. The aeronautical thruster according to claim 1 , wherein the downstream annular row comprises at least one group of blades having the same radial dimension, including at least a first group comprising a plurality of first blades and/or a second group comprising a plurality of second blades.

9. The aeronautical thruster according to claim 8 , wherein the blades of the at least one group of blades are arranged circumferentially such that they are contiguous within an angular sector around the longitudinal axis.

10. The aeronautical thruster according to claim 1 , wherein the first blade and the second blade are each arranged angularly around the longitudinal axis at a respective angle, the angle being measured clockwise around the longitudinal axis relative to an angular position at 12 o'clock, the radial dimension or the radially outer radius of the first blade and/or the radial dimension or the radially outer radius of the second blade being determined as a function of the respective angle, according to a linear, parabolic, logarithmic, or exponential law.

11. The aeronautical thruster according to claim 1 , wherein the downstream annular row comprises at least one set of blades arranged contiguously in an angular sector around the longitudinal axis, each blade of the set of blades being arranged angularly around the longitudinal axis at a respective angle, the angle being measured around the longitudinal axis in a clockwise direction relative to an angular position at 12 o'clock, each blade of the set of blades having a radial dimension or a radially outer radius determined as a function of the respective angle according to a linear, parabolic, logarithmic, or exponential law.

12. The aeronautical thruster according to claim 11 , wherein the angular sector associated with the set of blades extends between the angular position at 12 o'clock and an angular position at 6 o'clock.

13. The aeronautical thruster according to claim 1 , wherein the second blade is angularly positioned around the longitudinal axis closer to an angular position at 6 o'clock than the first blade.

14. The aeronautical thruster according to claim 1 , wherein the downstream annular row comprises at least one pair of blades for which the angular positioning around the longitudinal axis is symmetrical relative to a plane of symmetry comprising the longitudinal axis and the axis passing through angular positions at 6 o'clock and at 12 o'clock, and wherein the blades of the pair of blades have the same radial dimension.

15. The aeronautical thruster according to claim 1 , wherein the downstream annular row has a rotational symmetry of order n where n is an integer greater than or equal to 2.

16. The aeronautical thruster according to claim 1 , wherein the upstream annular row and the downstream annular row are located at an upstream end portion of the aeronautical thruster along the longitudinal direction, or at a downstream end portion of the aeronautical thruster along the longitudinal direction.

17. A propulsion assembly for an aircraft, comprising:
an aeronautical thruster according to claim 1 ; and
an attachment pylon for fixing the aeronautical thruster to the aircraft, the attachment pylon being connected to one of the blades of the downstream annular row to form a single aerodynamic assembly.

18. An aeronautical thruster having a longitudinal axis, comprising:
a hub; and
at least two annular rows of unducted blades having an upstream annular row and a downstream annular row which are spaced apart from each other along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade,
wherein the radially outer ends of the blades of the downstream annular row are inscribed within an outer envelope whose projection onto a plane normal to the longitudinal axis defines a circle.

19. An aeronautical thruster having a longitudinal axis, comprising:
a hub; and
at least two annular rows of unducted blades having an upstream annular row and a downstream annular row which are spaced apart from each other along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade,
wherein the first blade and the second blade are each arranged angularly around the longitudinal axis at a respective angle, the angle being measured clockwise around the longitudinal axis relative to an angular position at 12 o'clock, the radial dimension or the r

Assignees

• Safran Aircraft Engines

Inventors

• Gea Aguilera Fernando
• Binder Anthony
• Dubois Adrien Clément Marcel
• Gruber Mathieu Simon Paul
• Jodet Norman Bruno André
• Lebeault Eva Julie
• Regnard Josselin David Florian

Classifications

• B64C11/20

  Constructional features · CPC title

• B64C11/04

  Blade mountings · CPC title

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• B64C11/48 Primary

  Units of two or more coaxial propellers · CPC title