Hybrid rotor blade
AssigneeGeneral Electric Company
InventorsJohn J. Ciokajlo, Michael T. O'Brien
Life of this patent
Estimating the term…
Abstract
A hybrid gas turbine engine rotor blade includes an airfoil and a dovetail integrally joined thereto. The airfoil includes an inner portion disposed adjacent to the dovetail to provide a structural transition, and an outer portion disposed thereabove for effecting a pressure rise in airflow channeled thereacross. A nosepiece is disposed adjacent to the leading edge of the airfoil inner portion, and a tailpiece is disposed adjacent to the trailing edge of the airfoil inner portion. The nosepiece, tailpiece, and airfoil inner portion are collectively aerodynamically configured for effecting a pressure rise in the airflow channeled thereacross.
Claims9
A hybrid gas turbine engine rotor blade comprising:
- an airfoil having a leading edge and a trailing edge extending from a root to a tip defining therebetween first and second opposite sides;
- a dovetail integrally joined to said airfoil root for removably mounting said airfoil to a rotor disk;
- said airfoil having an inner portion disposed adjacent to said root, and an outer portion disposed adjacent to said tip, said airfoil outer portion being aerodynamically configured from said leading edge to said trailing edge for effecting a primary pressure rise in airflow channeled thereacross, and said airfoil inner portion being configured from said leading edge to said trailing edge to provide a structural transition from said airfoil outer portion to said dovetail;
- a nosepiece disposed adjacent to said leading edge of said airfoil inner portion;
- a tailpiece disposed adjacent to said trailing edge of said airfoil inner portion;
- and
- said nosepiece, said tailpiece, and said airfoil inner portion being collectively aerodynamically configured for effecting a secondary pressure rise in airflow channeled thereacross.
A hybrid gas turbine engine rotor comprising:
- a plurality of circumferentially spaced apart rotor blades each comprising:
- an airfoil having a leading edge and a trailing edge extending from a root to a tip defining therebetween first and second opposite sides;
- a dovetail integrally joined to said airfoil root for removably mounting said airfoil to a rotor disk;
- an inner platform abutting said airfoil inner portion adjacent to said dovetail to provide an inner flow boundary for said airflow channeled across said airfoil inner portion;
- an outer platform abutting said airfoil inner portion adjacent to said airfoil outer portion and spaced from said inner platform to provide an outer flow boundary for said airflow channeled across said airfoil inner portion;
- said airfoil having an inner portion disposed adjacent to said root, and an outer portion disposed adjacent to said tip, said airfoil outer portion being aerodynamically configured from said leading edge to said trailing edge for effecting a primary pressure rise in airflow channeled thereacross, and said airfoil inner portion being configured from said leading edge to said trailing edge to provide a structural transition from said airfoil outer portion to said dovetail;
- a nosepiece disposed adjacent to said leading edge of said airfoil inner portion;
- a tailpiece disposed adjacent to said trailing edge of said airfoil inner portion;
- and
- said nosepiece, said tailpiece, and said airfoil inner portion being collectively aerodynamically configured for effecting a secondary pressure rise in airflow channeled thereacross;
- an arcuate forward inner band fixedly joined to said plurality of nosepieces at inner ends thereof, and fixedly joined to said inner platforms at forward ends thereof;
- arcuate forward outer band fixedly joined to said plurality of nosepieces at outer ends thereof, and fixedly joined to said outer platforms at forward ends thereof;
- an arcuate aft inner band fixedly joined to said plurality of tailpieces at inner ends thereof, and fixedly joined to said inner platforms at aft ends thereof;
- and
- an arcuate aft outer band fixedly joined to said plurality of tailpieces at outer ends thereof, and fixedly joined to said outer platforms at aft ends thereof.
Dependencies are inferred from the claim text.