Shaft assembly for aircraft engine
AssigneePratt & Whitney Canada Corp.
InventorsMichel LABBE, Lukasz POKRZYWA
Life of this patent
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Abstract
There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
Claims20
An aircraft engine comprising:
- an engine shaft;
- a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis;
- and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.
A method of retaining a tower shaft and a quill shaft to one another comprising:
- transmitting a rotational input from an engine shaft of an aircraft engine to an engine accessory with a tower shaft and a quill shaft engaged to the tower shaft;
- sealing a connection between the quill shaft and the tower shaft with a first annular ring seal disposed between the quill shaft and the tower shaft;
- and
- upon removal of the engine accessory from the aircraft engine, retaining the quill shaft in engagement with the tower shaft with both the first annular ring seal and a second annular ring seal disposed between the quill shaft and the tower shaft and axially offset from the first annular ring seal.
A shaft assembly for an aircraft engine, comprising:
- a tower shaft drivingly engageable to an engine shaft of the aircraft engine;
- a quill shaft in driving engagement with the tower shaft and drivingly engageable to an engine accessory, the tower shaft concentrically partially received within the quill shaft;
- and at least two axially spaced apart annular ring seals disposed radially between the quill shaft and the tower shaft, the at least two annular ring seals biased against both of the tower shaft and the quill shaft.
Dependencies are inferred from the claim text.