Turbomachinery blade

{
  "publication_number": "US3694104A",
  "country": "US",
  "kind": "A",
  "title": "Turbomachinery blade",
  "abstract": "This turbomachinery blade has an internal frame or strut made of plastic-impregnated fibers and covered with a thin metal sheath. The frame has sections extending spanwise with the fiber rovings wound under tension which is maintained while the plastic is being cured. The sheath may be made in one or more sections to receive the assembled frame structure the parts being adhesively or otherwise joined into a unit. The frame sections have the fibers passed around mandrels to form loop type openings at the hub end for receiving pins by which the blades are retained in the hub or on a rotor disc. When the blades are assembled with a disc to form a rotor, suitable spacers are inserted between them to provide the platforms or inner boundaries for the air or gas passages.",
  "claims": [
    "1. A blade for turbomachinery comprising: a. a substantially hollow internal frame structure composed of a plurality of sections formed of plastic-impregnated fibers extending spanwise and wound under tension oriented spanwise of the blade; and b. a thin metal outer cover secured to and enclosing the frame structure, said frame structure and outer cover providing said blade with an airfoil shape.",
    "2. The blade for turbomachinery of claim 1 in which the sections of the internal frame structure extend spanwise of the blade.",
    "3. The blade for turbomachinery of claim 2 in which certain sections of the internal frame structure have interfitting overlapping portions.",
    "4. The blade for turbomachinery of claim 1 in which the assembled sections of the internal frame structure provide the latter with an airfoil shape.",
    "5. The blade for turbomachinery of claim 1 in which the assembled sections of the internal frame structure a hollow airfoil shape reinforced at intervals spaced chordwise of the blade with webs extending between pressure and suction side walls.",
    "6. The blade for turbomachinery of claim 1 which at least part of the sections have the hub ends formed by passing the tensioned fibers around a mandrel to form a loop-type opening for receiving a blade retaining pin.",
    "7. The blade for turbomachinery of claim 6 in which predetermined sections have the openings thereof located at different distances from the tip end of the section to receive a plurality of blade retaining pins disposed in an offset relationship.",
    "8. The blade for turbomachinery of claim 6 in which the mandrels around which the fibers are passed to form the retaining pin receiving openings are arranged to dispose the axes of the openings in a direction generally parallel to the mean line of the finished blade and make the fibers extend from the blade forming portion to the loop forming portion with a minimum of curvature.",
    "9. The blade for turbomachinery of claim 8 in which the axes of the openings of frame sections adjacent the leading edge portion of the blade are aligned generally with the mean line of the blade at the leading edge portion thereof adjacent the hub end.",
    "10. The blade for turbomachinery of claim 8 in which the axes of the openings of frame sections adjacent the trailing edge portion of the blade are aligned generally with the mean line of the blade at the trailing edge portion thereof adjacent the hub end.",
    "11. The blade for turbomachinery of claim 8 in which the axes of the openings of frame sections adjacent the leading and trailing edge portions of the blades are aligned generally with the mean line of the blade at the leading and trailing edge portions respectively thereof adjacent the hub end.",
    "12. The blade for turbomachinery of claim 11 in which blade retaining pins are adapted to be inserted from opposite edges of the blade.",
    "13. The blade for turbomachinery of claim 7 in which the frame sections adjacent one edge of the blade have the openings thereof disposed a greater distance from the tip end of the section than the openings of the frame sections adjacent the other edge of the blade.",
    "14. The blade for turbomachinery of claim 6 in which the thin metal outer layer extends around the blade retaining pin receiving loops.",
    "15. The blade for turbomachinery of claim 2 which the edge forming sections of the frame structure have substantially V-shaped cross-sections.",
    "16. The blade for turbomachinery of claim 15 in which the intermediate blade forming sections of the frame structure have substantially U-shaped cross-sections.",
    "17. The blade for turbomachinery of claim 16 in which the frame structure sections with the V-shaped cross-sections are arranged to form the leading and trailing edges of the blade.",
    "18. The blade for turbomachinery of claim 17 in which the frame structure sections with the U-shaped cross-sections are disposed with the base ends of the U shape between the legs of the vee shape of the other sections."
  ],
  "cpc": [
    "F01D 5/147",
    "F01D 5/282",
    "F01D 5/3053"
  ],
  "ipc": [
    "F01D 5/14",
    "F01D 5/28",
    "F01D 5/30"
  ],
  "assignees": [
    "Garrett Corp"
  ],
  "inventors": [
    "John R Erwin"
  ],
  "filing_date": "1970-10-07",
  "publication_date": "1972-09-26",
  "grant_date": "1972-09-26",
  "priority_date": "1970-10-07",
  "application_number": "US-3694104D-A",
  "family_id": "22145789",
  "cited_by_count": 96,
  "citations": [
    "US1452602A",
    "US2175204A",
    "US2635848A",
    "GB687507A",
    "US2980395A",
    "US2920866A",
    "US2916808A",
    "US2929755A",
    "US3051436A",
    "US3167129A",
    "US3333642A",
    "US3476484A"
  ]
}