# US 4,146,967 A · Rotor blade inspection fixture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 4,146,967 A - Document ID: US4146967A - Status: Granted - Kind: A - Application number: 05/824,405 - Filed: 1977-08-15 - Granted: 1979-04-03 - Earliest claimed: 1977-08-15 - Assignees: The Boeing Company - Inventors: Martin J. Rohner; George Olszewsky; Harry W. Hamilton - Web page: https://patentgrep.com/patent/US4146967A ## CPC - G01B 5/205: {of turbine blades or propellers} - G01B 5/0002: {Arrangements for supporting, fixing or guiding the measuring instrument or the object to be measured} - G01B 5/20: for measuring contours or curvatures - G01B 21/20: for measuring contours or curvatures, e.g. determining profile - G01B: MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS ## Abstract An apparatus for measuring the contour of rotor blades is provided. The apparatus or fixture of the present invention will measure airfoil shape and twist at any spanwise station along a rotor blade as well as measuring the chordwise and flapwise bow of the rotor blade. The fixture includes a base to which the blade is secured. A plate or templet like device is placed about the blade. The plate is secured to a carriage which is movable along the base so that it may traverse the blade along its span. Transducers connected to the plate measure the airfoil contour at particular spanwise stations. The plate is mounted to the carriage in such a manner that its rotation, vertical, and horizontal displacement may be measured and hence the twist, chordwise and flapwise bow may be determined. ## Claims ### Claim 1 An apparatus for determining the contours of a rotor blade having a pitch axis and having a multiplicity of airfoil sections along its span which comprises: a frame adapted to be detachably connected to a predetermined airfoil section along the span of the rotor blade, the airfoil sections including a reference line passing substantially from the leading edge to the trailing edge of the airfoil, said frame being adapted to pivot about a line which is substantially coincident with the rotor blade pitch axis to enable said frame to be aligned with said reference line; a first measuring means connected to said frame for determining the distance a preselected point on the surface of the rotor blade is located from the leading edge of said airfoil section along a line parallel to said reference line; and a second measuring means connected to said frame for determining the distance said preselected point is located from said reference line along a line perpendicular to said reference line. ### Claim 2 (depends on 1) The apparatus of claim 1 wherein: said first measuring means is adapted so as to permit it to move with respect to the airfoil section along a line substantially parallel to said reference line; and said second measuring means is adapted so as to permit it to move with respect to said airfoil section along a line substantially parallel to said line perpendicular to said reference line; thereby permitting the determination of the location of a multiplicity of points along the surface of the airfoil thus determining its contour. ### Claim 3 (depends on 2) The apparatus of claim 2 wherein said second measuring means is slidably connected to said first measuring means. ### Claim 4 (depends on 2) The apparatus of claim 2 which further includes: a base having means for supporting the rotor blade; a trolley, slidably connected to said base, having said frame connected thereto, said trolley being adapted to move along the span of the blade, thereby permitting said frame to be positioned at preselected airfoil sections along the span of the blade. ### Claim 5 (depends on 1) The apparatus of claim 1 which further includes: a base having means for supporting the rotor blade; a trolley, slidably connected to said base, having said frame connected thereto, said trolley being adapted to move along the span of said blade, thereby permitting said frame to be positioned at preselected airfoil sections along the span of the blade. ### Claim 6 (depends on 5) The apparatus of claim 5 which further includes a third measuring means connected to said base for measuring the distance said frame is located from a second preselected reference point along a line substantially parallel to the rotor blade pitch axis. ### Claim 7 (depends on 6) The apparatus of claim 6 wherein said frame is pivotally connected to said trolley to permit said frame to pivot with respect to said trolley about a line which is substantially coincident with the rotor blade pitch axis. ### Claim 8 (depends on 7) The apparatus of claim 7 which further includes a fourth measuring means connected to said trolley for measuring the magnitude of the angular rotation of said frame with respect to said trolley from a third predetermined reference point, thereby permitting the magnitude of the angle of said reference line to a predetermined reference line located in a plane parallel to the airfoil section chord plane to be determined. ### Claim 9 (depends on 8) The apparatus of claim 8 which further includes means for permitting said frame to move with respect to said trolley, connected to said frame and to said trolley, along a vertical line. ### Claim 10 (depends on 9) The apparatus of claim 9 which further includes a fifth measuring means connected to said trolley for measuring the distance said frame has moved vertically, thereby permitting a determination of the magnitude of the chordwise bow of the rotor blade. ### Claim 11 (depends on 9) The apparatus of claim 9 which further includes means for permitting said frame to move horizontally with respect to said trolley, connected to said frame and to said trolley. ### Claim 12 (depends on 11) The apparatus of claim 11 which further includes a sixth measuring means connected to said trolley for measuring the distance said frame has moved horizontally, thereby permitting a determination of the magnitude of the flapwise bow of the rotor blade. ### Claim 13 An apparatus for determining the contours of a rotor blade having a pitch axis, a multiplicity of airfoil sections along its span wherein each airfoil section has a reference line passing substantially from the leading edge to the trailing edge which comprises: a base having means for supporting the rotor blade; a frame adapted to be detachably connected to a predetermined airfoil section along the span of the rotor blade; a trolley slidably connected to said base for movement along the span of the rotor blade and having said frame connected thereto by means permitting, said frame to pivot with respect to said trolley about a line which is substantially coincident with the rotor blade pitch axis, said frame to move vertically with respect to said trolley said frame to move horizontally with respect to said trolley a first measuring means connected to said frame so as to permit it to move with respect to the airfoil section in a direction substantially parallel to said reference line, for determining the distance a preselected point located on the surface of the airfoil is located from the leading edge of said airfoil section along a line parallel to said reference line; a second measuring means connected to said frame for determining the distance said preselected point is located from said reference line along a line perpendicular to said reference line, said second measuring means being connected to said frame so as to permit it to move with respect to said airfoil section along a line substantially paralled to said line perpendicular to said reference line, thereby permitting the determination of the location of a multiplicity of points along the surface of the airfoil thus determining its contour; a third measuring means connected to said base for measuring the distance said frame is located from a preselected reference point along a line substantially parallel to the rotor blade pitch axis; a fourth measuring means connected to said trolley for measuring the magnitude of the angular rotation of said frame with respect to said trolley from a predetermined reference line, thereby permitting the magnitude of the angle of said reference line of said airfoil section to said predetermined reference line to be determined; a fifth measuring means connected to said trolley for measuring the distance said frame has moved vertically a predetermined point along said reference line of said, thereby permitting a determination of the chordwise bow of the rotor blade; and a sixth measuring means connected to said trolley for measuring the distance said frame has moved horizontally to a predetermined point along a line perpendicular to, thereby permitting a determination of the magnitude of the flapwise bow of the rotor blade.