Hybrid drive engine
First Claim
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1. A disk stack for an engine comprising:
- a plurality of disks;
each disk having a body defining a closed-figure airfoil comprising;
an upper surface and a lower surface;
a central opening;
an inner perimeter defined by the central opening; and
an outer perimeter radially outward of the inner perimeter;
the closed-figure airfoil having a cross-section comprising;
a line defining the lower surface; and
a convex line defining the upper surface and reaching a zenith that is a highest point on the airfoil section of the disk;
a spacer situated within the central opening of each disk;
an axis of revolution substantially normal to first and second planes defined by the inner perimeter and the outer perimeter of the disk; and
a separator lip on the upper surface of the disk and located proximate the outer perimeter of the disk, the separator lip extending along a narrow ridge that is higher than the immediately adjacent portion of the upper surface.
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Accused Products
Abstract
A hybrid drive engine uses air foil shaped disks of a first configuration for a compressor portion thereof and air foil shaped disks of a second configuration for a turbine portion thereof, whereby the disks exhibit aerodynamic effects of lift. Particularly, the compressor disks are configured to cause aerodynamic lift off of a periphery of the disks, while the turbine disks are configured to cause aerodynamic lift off of an inner hole of the disks. The aerodynamic nature of the disks cause each disk thereof to form two opposing airfoil shapes either head to head or trailing edge to trailing edge across the through hole.
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Citations
31 Claims
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1. A disk stack for an engine comprising:
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a plurality of disks; each disk having a body defining a closed-figure airfoil comprising; an upper surface and a lower surface; a central opening; an inner perimeter defined by the central opening; and an outer perimeter radially outward of the inner perimeter; the closed-figure airfoil having a cross-section comprising; a line defining the lower surface; and a convex line defining the upper surface and reaching a zenith that is a highest point on the airfoil section of the disk; a spacer situated within the central opening of each disk; an axis of revolution substantially normal to first and second planes defined by the inner perimeter and the outer perimeter of the disk; and a separator lip on the upper surface of the disk and located proximate the outer perimeter of the disk, the separator lip extending along a narrow ridge that is higher than the immediately adjacent portion of the upper surface. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A disk stack for an engine comprising:
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a plurality of disks; each disk having an annular body defining an airfoil with; an upper surface and a lower surface; an axis of revolution; a projected reference plane that is normal to the axis of revolution; an inner and outer perimeter; and a reference chord line passing through the inner and outer perimeters; each airfoil configured with a negative airfoil angle such that revolution of the reference chord defines an angled surface of a frustum of a cone, whereby during revolution a forward portion of the airfoil is at a lower angle of incidence to incoming air than a remainder of the airfoil thereby compensating for air downwash effects from the forward portion of the airfoil and balancing the aerodynamic lift fore and aft on the disk, the airfoil having a cross section presenting a low aerodynamic drag to a flow of air generally parallel to the projected reference plane. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20)
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21. An engine comprising:
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a housing; a compressor section disposed in the housing and comprising a compressor disk stack of a plurality of annular compressor disks having a compressor disk body defining a closed-figure airfoil; a turbine section disposed in the housing and in communication with the compressor section, the turbine section comprising a turbine disk stack of a plurality of annular turbine disks having a turbine disk body defining a closed-figure airfoil; and a central shaft mechanically linking the turbine disk stack with the compressor disk stack wherein the closed-figure airfoil defining the body of each disk of the compressor and turbine disk stacks comprises; an upper surface and a lower surface; a central opening; an inner perimeter defined by the central opening; an outer perimeter radially outward of the inner perimeter; a cross-section comprising; a line defining the lower surface; and a convex line defining the upper surface and reaching a zenith that is a highest point on the airfoil of the disk; and a separator lip on the upper surface of the disk and located proximate the outer perimeter of the disk, the separator lip extending along a narrow ridge that is higher than the immediately adjacent portion of the upper surface. - View Dependent Claims (22, 23, 24, 25, 26, 27, 28, 29, 30, 31)
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Specification