CN-122029101-A - Guide bar support housing

Abstract

A fan hub (19) comprising a central body (17) extending axially between an upstream side (25) and a downstream side (26), the central body (17) having a plurality of radial ports (20), each radial port being configured to hold a fan blade in place. The fan hub (19) comprises an upstream annular housing (18) secured to the upstream side (25) via a bolted joint.

Inventors

• SMITH, JEREMY
• Julian Lemaine

Assignees

• 赛峰飞机发动机公司

Dates

Publication Date

20260512

Application Date

20240926

Priority Date

20231011

Claims (10)

1. 1. A fan hub (19) comprising a central body (17) extending axially between an upstream side (25) and a downstream side (26), the central body (17) having a plurality of radial ports (20), each configured to hold a fan blade in place, characterized in that the fan hub (19) comprises an upstream annular housing (18) secured to the upstream side (25) via a bolted joint.
2. 2. Fan hub (19) according to claim 1, wherein the central body (17) and the upstream annular housing (18) are each independently made by forging.
3. 3. Fan hub (19) according to claim 1 or 2, comprising at least two tangential force absorbing yokes (35, 36) fixed to the upstream annular housing (18), at least one tangential force absorbing yoke (35, 36) being a spare yoke.
4. 4. A fan hub (19) according to claim 3, wherein the tangential force absorbing yoke (35, 36) is fixed to the upstream annular housing (18) by welding.
5. 5. A fan hub (19) according to claim 3, wherein the tangential force absorbing yoke (35, 36) is fixed to the upstream annular housing (18) by a bolted joint.
6. 6. Fan hub (19) according to claim 1 or 2, comprising at least two tangential force absorbing yokes (35, 36) forming a one-piece part with the upstream annular housing (18), at least one tangential force absorbing yoke (35, 36) being a spare yoke.
7. 7. A fan hub (19) according to any of claims 1 to 6, wherein the central body (17) comprises titanium.
8. 8. Aircraft engine, characterized in that it comprises a fan hub (19) according to any one of claims 1 to 7.
9. 9. A method for manufacturing a fan hub (19) according to any of claims 1 to 7, characterized in that the method comprises the steps of: -manufacturing said central body (17) and said upstream annular housing (18) from two blocks of material (15, 16), -Fixing the upstream annular housing (18) to the central body (17) via a bolted joint.
10. 10. The method according to claim 9, wherein the step of manufacturing the central body (17) and the upstream annular housing (18) is performed by forging and comprises a heat treatment operation, the method further comprising an operation of fixing at least two tangential force absorbing yokes (35, 36) to the upstream annular housing (18), unless the yokes (35, 36) form a single piece with the upstream annular housing (18).

Description

Guide bar support housing Technical Field The present invention relates to a component of the "fan hub" type, which corresponds to a fan disk, and to a method for manufacturing a component of the "fan hub" type. In particular, the invention relates to the manufacture of a fan hub with a bolted joint (bolted joint). Background The fan hub of an aircraft engine (a type of component equivalent to a fan disk on a conventional turbine) is able to support the blades of the fan, which extend radially beyond the fan hub to form the fan, as well as some bearings. The fan hub allows engine torque to be transferred to the blades, the fan hub being additionally connected to an engine shaft of the aircraft engine. Thus, the fan hub ensures propulsion together with the blades and a blade setting system in the centre of the fan hub, which is directly connected to the root of each blade and orients the blades according to the input setpoint. To ensure the safety of the aircraft and its passengers, the fan hubs are subject to major manufacturing limitations. In particular, the mechanical properties of the fan hub must be protected against any breakage of the material constituting the fan hub and/or any other unsafe influences. The criteria for damage tolerance are one of the main criteria to be met. In general, there are two manufacturing techniques for manufacturing a fan hub. The first technique includes casting embodiments and forming by conventional machining operations, while the second technique includes forging embodiments and forming by conventional machining operations. For both techniques, the fan hub is manufactured as a single piece and machining operations are performed in a block (block) obtained after casting or forging. The first implementation by casting allows for the manufacture of more complex shapes that more closely approximate the requirements of a fan hub. Furthermore, the amount of material required can be optimized, thereby reducing costs associated with the amount of material. This technique requires less machining because machining requires only precise surface and interface finishing and is easy to implement. However, the material is not yet sufficient in terms of mechanical strength. The second implementation by forging requires starting from a mass of material having a volume greater than that of the final product, which means high material costs. In addition, the forging process does not remove a lot of material as casting does nor produce an optimized complex shape, making the resulting hub more bulky. However, forging achieves the excellent mechanical properties of the material necessary for manufacturing the fan hub, which is necessary because it ensures that the manufacture of the fan hub meets the safety standards required in the aerospace environment. The second method has other drawbacks such as the need to find a capable forging mill, and degradation of material properties at the center of the mass. In practice, this second method involves a step of heat-treating the block of material, which, due to the excessive thickness of the block, causes the properties of the material located on the outside of the block to change differently from those of the material located on the inside. This weakens the mechanical properties of the hub material and thus adversely affects the flight safety of the aircraft. The prior art according to the second method is basically illustrated using fig. 1 to 4, which are part of a set of diagrams to be explained later. In fig. 1, a partial section of a fan 1 implanted in an aircraft engine 2 can be seen. The fan 1 comprises a hub 3, a central body 4 of the hub 3 extending axially between an upstream side 5 and a downstream side 6. The upstream extension 7 extends from the upstream side portion 5 in one direction of the axial direction D of the hub 3, and the downstream extension 8 extends from the downstream side portion 6 in the opposite direction of the axial direction D of the hub 3. Fig. 2 shows the hub 3 in a perspective view, and fig. 3 also shows a part of the hub 3 in a perspective view. Fig. 4 shows schematically in a cross-section a block of material 9 from which the hub 3 of the fan 1 is forged. These figures make it possible to realise a bulky aspect of the hub 3. Disclosure of Invention The present invention seeks to overcome the above-mentioned drawbacks and to provide a fan hub which meets the criteria for ensuring flight safety and whose production costs allow its industrial production. More precisely, it is an object of the invention to improve, inter alia, the mechanical strength of the hub. The present invention is also directed to reducing the mass of the pitch setting system to improve engine mass balance. The invention also aims to limit metallurgical health effects on the hub. The present invention also seeks to optimize the industrialization of the components by limiting manufacturing risks and additional industrialization costs. Finall