Patent ID: 11873118

Abstract:
This invention relates to both process and tooling for machining exemplary Hamilton Sundstrand 7111 and 7121 aircraft propeller blade taper bores, or equivalent to comply with government and or industry standards or specifications for such refurbishment. The tooling and process invented are an Improvement over previous and current taper bore machining methods in improved repeatability and cost effectiveness, as this machining method can quickly and repeatedly machine propeller blades to meet fit, form, and function requirements. The process makes use of a specially constructed horizontal mill, specially constructed blade-holding fixture, specially constructed probing system, specially constructed reamers, and specially constructed air gauges. A blade holding fixture assembly including a base plate, a blade holding fixture and a blade alignment fixture hold an aircraft propeller blade in a horizontal milling machine for refurbishment of the taper bores. Refurbishment includes reaming shot peened surfaces, testing the reamed surfaces with an air gauge and a fluorescent penetrant emersion fixture.