View source for 18573835. FAN MODULE IMPELLER, AND JET TURBINE ENGINE EQUIPPED WITH SUCH AN IMPELLER simplified abstract (SAFRAN AIRCRAFT ENGINES)

=FAN MODULE IMPELLER, AND JET TURBINE ENGINE EQUIPPED WITH SUCH AN IMPELLER=


==Organization Name==

[[:Category:SAFRAN AIRCRAFT ENGINES|SAFRAN AIRCRAFT ENGINES]]


[[Category:SAFRAN AIRCRAFT ENGINES]]

==Inventor(s)==

[[:Category:Sylvain Huchet of Moissy-Cramayel (FR)|Sylvain Huchet of Moissy-Cramayel (FR)]][[Category:Sylvain Huchet of Moissy-Cramayel (FR)]]

[[:Category:Didier Queant of Moissy-Cramayel (FR)|Didier Queant of Moissy-Cramayel (FR)]][[Category:Didier Queant of Moissy-Cramayel (FR)]]

==FAN MODULE IMPELLER, AND JET TURBINE ENGINE EQUIPPED WITH SUCH AN IMPELLER - A simplified explanation of the abstract==


This abstract first appeared for US patent application 18573835 titled 'FAN MODULE IMPELLER, AND JET TURBINE ENGINE EQUIPPED WITH SUCH AN IMPELLER

'''Simplified Explanation:'''
The turbojet engine fan module wheel described in the patent application consists of blades made of composite material, each with a unique base design that allows for secure assembly and retention within the wheel structure.

* Each blade has a root that is assembled with a base distinct from the bases of other blades.
* The base of each blade features a groove that opens out on both the upstream and downstream faces, allowing for axial interlocking with the root of the blade.
* The root is retained on the base along radial, circumferential, and axial directions, ensuring stability and structural integrity.
* Each base also includes a part that blocks the root axially within the groove, further enhancing the retention of the blade within the wheel module.

'''Key Features and Innovation:'''
* Blades made of composite material with unique base designs for secure assembly.
* Axial interlocking mechanism between the root of the blade and the base for retention.
* Groove on the base opening out on both faces for effective interlocking.
* Axial blocking part on the base to secure the root within the groove.
* Enhanced stability and structural integrity of the turbojet engine fan module wheel.

'''Potential Applications:'''
The technology described in the patent application can be applied in:
* Aircraft turbojet engines
* Industrial gas turbines
* Marine propulsion systems

'''Problems Solved:'''
* Ensures secure assembly and retention of blades in the fan module wheel.
* Enhances stability and structural integrity of the turbojet engine components.

'''Benefits:'''
* Improved performance and efficiency of turbojet engines.
* Reduced maintenance and replacement costs.
* Enhanced safety and reliability of engine components.

'''Commercial Applications:'''
Potential commercial uses include:
* Aircraft manufacturing companies
* Gas turbine manufacturers
* Aerospace industry suppliers

'''Questions about Turbojet Engine Fan Module Wheel:'''
1. How does the unique base design of each blade contribute to the overall performance of the turbojet engine fan module wheel?
2. What are the specific advantages of using composite material for the blades in terms of durability and efficiency?


==Original Abstract Submitted==

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.



[[Category:F02K7/00]]
[[Category:F02K3/06]]
[[Category:CPC_F02K7/005]]