Fan module impeller, and jet turbine engine equipped with such an impeller

Patent metadata

Field	Value
Publication number	US-12305593-B2
Application number	US-202218573835-A
Country	US
Kind code	B2
Filing date	Jun 20, 2022
Priority date	Jun 23, 2021
Publication date	May 20, 2025
Grant date	May 20, 2025

Abstract

Turbojet engine fan module wheel, including a plurality of blades made of composite material, each blade having a root assembled with a base distinct from the bases of the other blades, each base having a groove extending axially and opening out on the side of the upstream face and on the side of the downstream face, each root cooperating by axial interlocking in a form-fitting manner, for example in the shape of a dovetail, with the groove of the base, whereby the root is retained on the base along the radial and circumferential directions, and each base cooperates with at least one part configured to axially block the root within the groove of the base, whereby the root is retained along the axial direction.

First claim

The invention claimed is:

1. A turbojet engine fan module wheel, having an axial direction, a radial direction and a circumferential direction, an upstream face and a downstream face, the wheel comprising a plurality of blades made of fiber-reinforced organic-matrix composite material, each blade of the plurality of blades having a root assembled with a base distinct from the bases of the other blades of the plurality of blades, each of the respective bases having a groove extending axially and opening out on a side of the upstream face and/or on a side of the downstream face, each of the respective roots cooperating by axial interlocking in a form-fitting manner, optionally in a shape of a dovetail, with the respective grooves of the respective bases, whereby the respective root is retained on the respective base along the radial direction and the circumferential direction, and each of the respective bases cooperates with at least one part configured to axially block the respective root within the respective groove of the respective base, whereby the respective root is retained along the axial direction, wherein the plurality of blades are variable pitch blades, each of the respective bases being mounted on the at least one part configured to axially block the respective root within the respective groove of the respective base, wherein the at least one part is a single part distinct from the single parts of the other bases, each of the at least one part being configured to pivot around the radial direction, wherein each root of the plurality of blades and each of the respective grooves extend along the radial direction of the plurality of blades and the fan module wheel, each of the single parts comprises an annular collar which is fixed to a corresponding annular flange of each of the respective bases using fasteners extending longitudinally in the radial direction.

2. The turbojet engine fan module wheel according to claim 1 , wherein each of the single parts comprises a cavity receiving at least one piece of the respective base, the walls of the cavity blocking the respective groove on the side of the upstream face and on the side of the downstream face, whereby the respective root is retained along the axial direction.

3. The turbojet engine fan module wheel according to claim 1 , wherein each of the respective flanges extend along the axial direction and the circumferential direction.

4. The turbojet engine fan module wheel according to claim 3 , wherein each of the annular flanges is separated into two pieces by a central axial slot located in line with the groove, wherein the groove opens out into the central axial slot.

5. The turbojet engine fan module wheel according to claim 1 , wherein the root of each of the respective blades and the groove of each of the respective bases have a same axial length.

6. The turbojet engine fan module wheel according to claim 1 , wherein the wheel is a turbojet engine fan wheel.

7. A turbojet engine comprising the turbojet engine fan module wheel according to claim 1 .

8. The turbojet engine fan module wheel according to claim 1 , wherein each blade of the plurality of blades comprises a single base.

9. The turbojet engine fan module wheel according to claim 1 , wherein the at least one part is common between each of the blades of the plurality of blades.

10. The turbojet engine fan module wheel according to claim 1 , wherein a tip of each blade comprises at least one second part identical to the at least one part.

11. The turbojet engine fan module wheel according to claim 1 , further comprising a shim between a bottom of the groove and a tip of each blade, wherein the shim has a curved banana shape, a shape curved like a tile along a transverse direction or a rectilinear L shape, or a combination of shapes, wherein the shim is interposed between the root of each blade and the groove without modifying a structure of each of the blades.

Assignees

• Safran Aircraft Engines

Inventors

• Huchet Sylvain
• Queant Didier

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/3015

  with side plates · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• B64C11/08

  for non-adjustable blades · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title