| 摘要 |
PURPOSE: To provide a hybrid rotor blade of a gas turbine engine which can increase fuel consumption rate without modifying an existing design. CONSTITUTION: This hybrid rotor blade 20 for a gas turbine engine includes an airfoil 24 and a dovetail 38 integrally joined thereto. The airfoil 24 includes an inner portion 24a disposed adjacent to the dovetail 38 to form a structural transition, and an outer portion 24b disposed above the inner portion 24a for effecting a pressure rise in airflow passing through the outer portion 24b. A nosepiece 40 is disposed adjacent to the leading edge 26 of the airfoil inner portion 24a, and a tailpiece 42 is disposed adjacent to the trailing edge 28 of the airfoil inner portion 24a. The nosepiece 40, the tailpiece 42, and the airfoil inner portion 24a are collectively aerodynamically configured for effecting a pressure rise in the airflow passing therethrough. |
