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US 12,612,863 B2Granted
Test blade for gas turbine engine and method of making
AssigneePratt & Whitney Canada Corp.
InventorsMasoud Roshan Fekr, Rana Foroutan
Life of this patent
Estimating the term…
Abstract
A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having a first inner opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the first inner opening extends from and is located within two second inner openings, one of which extends from the leading edge of the root portion and the other extends from the trailing edge of the root portion.
Claims17
A test blade for a blade release test, comprising:
- an airfoil extending radially from a platform;
- and
- a root portion secured to the platform, the root portion having a first inner opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, the first inner opening extending from and is located within two second inner openings, one of which extends from the leading edge of the root portion and the other extends from the trailing edge of the root portion, and an elongated slot located on either the leading edge of the root portion or the trailing edge of the root portion, the elongated slot does not extend completely to the first inner opening such that a portion of the root portion defining at least one of the two second inner openings is located between the elongated slot and the first inner opening, wherein a blade-off segment comprising the airfoil, the platform and a top portion of the root portion is configured to separate from other portions of the root portion when the test blade is rotated at a predetermined speed during the blade release test.
Dependencies are inferred from the claim text.