Composite reinforced rotor

1. A component of a rotor system, comprising:

a disk comprising an airfoil element, a web extending radially inwardly from the airfoil element, a first arm element extending axially forwardly from the web with a first ring retaining feature and a second arm element extending axially aft from the web with a second ring retaining feature; and

first and second reinforcing rings formed of fiber reinforced materials and disposed to fit about the first and second arm elements, respectively,

wherein the first and second reinforcing rings have conical shapes characterized with uppermost surfaces which are level with the upper edges of the first and second ring retaining features, respectively, and decreasing radial thickness with respectively increasing forward and aft axial distances from the web and the first and second arm elements have conical shapes complementing the conical shapes of the first and second reinforcing rings, respectively.

2. The component of the rotor system according to claim 1 , wherein:

the airfoil element comprises a platform having a radially interior surface from which the web extends radially inwardly and a radially exterior surface and an airfoil extending radially outwardly from the radially exterior surface,

the web comprises a main member extending radially inwardly from the airfoil element, and

the component of the rotor system further comprises a bore, which is disposed at a distal end of the main member.

3. The component of the rotor system according to claim 2 , wherein the bore radially accommodates a hub or rotor element.

4. The component of the rotor system according to claim 1 , wherein the fiber reinforced materials comprise carbon fiber reinforced epoxy.

5. A component of a rotor system, comprising:

a disk comprising:

an airfoil element;

a web extending radially inwardly from the airfoil element;

a first arm element extending axially forwardly from the web and comprising a first ring retaining feature;

a second arm element extending axially aft from the web and comprising a second ring retaining feature; and

a bore, which has a maximum width that is narrower than a minimum width of the airfoil element; and

first and second reinforcing rings formed of fiber reinforced materials, the first and second reinforcing rings being disposed to fit about the first and second arm elements, respectively, and to be axially retained by the first and second ring retaining features, respectively,

wherein the first and second reinforcing rings have conical shapes characterized with uppermost surfaces which are level with the upper edges of the first and second ring retaining features, respectively, and decreasing radial thickness with respectively increasing forward and aft axial distances from the web and the first and second arm elements have conical shapes complementing the conical shapes of the first and second reinforcing rings, respectively.

6. The component of the rotor system according to claim 5 , wherein:

the airfoil element comprises a platform having a radially interior surface from which the web extends radially inwardly and a radially exterior surface and an airfoil extending radially outwardly from the radially exterior surface and comprising a tip defining the minimum width of the airfoil element,

the web comprises a main member extending radially inwardly from the airfoil element, and

the bore is disposed at a distal end of the main member.

7. The component of the rotor system according to claim 5 , wherein the fiber reinforced materials comprise carbon fiber reinforced epoxy.

8. A gas turbine engine, comprising compressor and turbine sections and components according to the component of claim 5 disposed in the compressor and turbine sections.

9. The gas turbine engine according to claim 8 , wherein the fiber reinforced materials of the reinforcing rings of each component of the rotor system vary with increasing aft positioning along a centerline such that capabilities of the fiber reinforced materials of the reinforcing rings of each component of the rotor system to withstand high-temperatures and high-pressures increase with increasing aft positioning along the centerline.

10. A component of a rotor system having a rotor or hub element, the component of the rotor system comprising:

a disk comprising an airfoil element, a web extending radially inwardly from the airfoil element and first and second arm elements extending axially forwardly and aft from the web, respectively, with first and second ring retaining features;

a bore disposed at an end of the web; and

first and second reinforcing rings formed of fiber reinforced materials and disposed to fit about the first and second arm elements, respectively,

wherein the web has a length that positions the bore to radially accommodate the rotor or hub element with radial space between the bore and the rotor or hub element,

wherein the first and second reinforcing rings have conical shapes characterized with uppermost surfaces which are level with the upper edges of the first and second ring retaining features, respectively, and decreasing radial thickness with respectively increasing forward and aft axial distances from the web and the first and second arm elements have conical shapes complementing the conical shapes of the first and second reinforcing rings, respectively.

11. The component of the rotor system according to claim 10 , wherein:

the airfoil element comprises a platform having a radially interior surface from which the web extends radially inwardly and a radially exterior surface and an airfoil extending radially outwardly from the radially exterior surface,

the web comprises a main member extending radially inwardly from the airfoil element, and

the bore is disposed at a distal end of the main member.

12. The component of the rotor system according to claim 10 , wherein the fiber reinforced materials comprise carbon fiber reinforced epoxy.

13. A gas turbine engine, comprising compressor and turbine sections and components according to the component of claim 10 disposed in the compressor and turbine sections.

14. The gas turbine engine according to claim 13 , wherein the fiber reinforced materials of the reinforcing rings of each component of the rotor system vary with increasing aft positioning along a centerline such that capabilities of the fiber reinforced materials of the reinforcing rings of each component of the rotor system to withstand high-temperatures and high-pressures increase with increasing aft positioning along the centerline.