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US 5,310,318 AGranted
Asymmetric axial dovetail and rotor disk
AssigneeGeneral Electric Company
InventorsAndrew J. Lammas, Nicholas J. Kray, Doug A. Finkhousen
Life of this patent
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Abstract
A rotor disk includes a rim with axially spaced apart forward and aft ends, with the aft end having a larger diameter than the forward end. The rim includes a plurality of straight dovetail slots defining dovetail posts therebetween. Each dovetail post includes a pair of lobes, a neck, and first and second pressure faces facing radially inwardly from the lobes. The first and second pressure faces vary in radial height therebetween from a first magnitude at the rim aft end to a second and smaller magnitude at the rim forward end to shift a portion of the bending loads from the dovetail post at the rim forward end to the dovetail post at the larger rim aft end.
Claims12
A gas turbine engine rotor disk comprising:
- an annular rim having an axial centerline axis and axially spaced apart forward and aft ends, said aft end having a larger diameter than said forward end;
- said rim having a plurality of circumferentially spaced apart, axially extending straight dovetail slots for receiving therein complementary dovetails of rotor blades, said slots defining a plurality of circumferentially spaced apart dovetail posts;
- and
- each of said posts comprising:
- a pair of circumferentially oppositely extending lobes defining a maximum circumferential width of said post;
- a neck disposed radially below said lobes and defining a minimum circumferential width of said post;
- a first pressure face facing radially inwardly from a respective one of said lobes to said neck on a first side of said post for reacting force from said dovetail;
- a second pressure face facing radially inwardly from the other one of said lobes to said neck on a second, opposite circumferential side of said post for reacting force from said dovetail;
- and
- said first and second pressure faces varying in radial height therebetween from a first magnitude at said rim aft end to a second magnitude at said rim forward end, said second magnitude being less than said first magnitude.
7 more elements
A gas turbine engine rotor blade having a longitudinal axis and comprising:
- an airfoil having a leading edge and a trailing edge;
- a dovetail extending from said airfoil and configured for axial entry into a rotor disk having a plurality of circumferentially spaced apart axial dovetail slots defining a plurality of circumferentially spaced apart dovetail posts, each post having a pair of radially inwardly facing, circumferentially spaced apart pressure faces;
- said dovetail having a pair of circumferentially extending lobes with upwardly facing pressure faces for transmitting loads to said rotor disk through said dovetail post pressure faces;
- and
- said dovetail being straight from adjacent said airfoil leading edge to adjacent said airfoil trailing edge and having a substantially constant configuration therebetween, with said pair of dovetail lobe pressure faces being longitudinally spaced apart from each other.
2 more elements
A rotor blade for a gas turbine engine rotor disk including:
- an annular rim having an axial centerline axis and axially spaced apart forward and aft ends, said aft end having a larger diameter than said forward end;
- said rim having a plurality of circumferentially spaced apart, axially extending straight dovetail slots for receiving therein complementary dovetails of rotor blades, said slots defining a plurality of circumferentially spaced apart dovetail posts;
- and
- each of said posts comprising:
- a pair of circumferentially oppositely extending lobes defining a maximum circumferential width of said post;
- a neck disposed radially below said lobes and defining a minimum circumferential width of said post;
- a first pressure face facing radially inwardly from a respective one of said lobes to said neck on a first side of said post for reacting force from said dovetail;
- a second pressure face facing radially inwardly from the other one of said lobes to said neck on a second, opposite circumferential side of said post for reacting force from said dovetail;
- and
- said first and second pressure faces varying in radial height therebetween from a first magnitude at said rim aft end to a second magnitude at said rim forward end, said second magnitude being less than said first magnitude;
- said rotor blade comprising:
- an airfoil having a leading edge and a trailing edge;
- a dovetail extending from said airfoil and configured for axial entry into a respective one of said dovetail slots;
- said dovetail having a pair of circumferentially extending lobes with upwardly facing pressure faces for transmitting loads to said rotor disk;
- and
- said dovetail being straight from adjacent said airfoil leading edge to adjacent said airfoil trailing edge and having a substantially constant configuration therebetween, with said pair of pressure faces being longitudinally spaced apart from each other.
13 more elements
Dependencies are inferred from the claim text.