Process for producing a new edge on an airfoil blade particularly the fan blade for a gas turbine engine

Patent · Tue Feb 03 04:00:00 EST 1987

OSTI ID:6777673

Sharon, H M

A process is described for forming a thinner leading edge on a fan blade comprising the steps of: (a) providing a first cutting means and a second cutting means; (b) providing a fan blade having a first side surface and a second side surface, the surfaces meeting to define a leading edge; and, (c) during a first cutting operation, forming a first cut surface using the first cutting means to produce a desired angle and fan blade thickness, by removing material from a portion of the first side surface adjacent the leading edge; and then, (d) during a second cutting operation, simultaneously forming second cut surfaces using the second cutting means to produce an aerodynamically efficient contour by removing material at the leading edge from both the first cut surface and the second side surface, by guiding the second cutting means along the leading edge and engaging both a portion of the first cut surface and a portion of the second side surface.

• Assignee: United Technologies Corp., Hartford, CT
• Patent Number(s): US 4639991
• OSTI ID: 6777673
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AERODYNAMICS
AIRFOILS
BLOWERS
CUTTING
DIMENSIONS
ENGINES
FLUID MECHANICS
GAS TURBINE ENGINES
HEAT ENGINES
INCIDENCE ANGLE
INTERNAL COMBUSTION ENGINES
MACHINING
MECHANICS
SURFACES
THICKNESS
TURBINE BLADES