FR1395148A - Manufacturing process of a bladed stator - Google Patents

Manufacturing process of a bladed stator

Info

Publication number
FR1395148A
FR1395148A FR971256A FR971256A FR1395148A FR 1395148 A FR1395148 A FR 1395148A FR 971256 A FR971256 A FR 971256A FR 971256 A FR971256 A FR 971256A FR 1395148 A FR1395148 A FR 1395148A
Authority
FR
France
Prior art keywords
manufacturing process
bladed stator
bladed
stator
manufacturing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
FR971256A
Other languages
French (fr)
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Stalker Corp
Original Assignee
Stalker Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US273455A external-priority patent/US3284881A/en
Application filed by Stalker Corp filed Critical Stalker Corp
Priority to FR971256A priority Critical patent/FR1395148A/en
Application granted granted Critical
Publication of FR1395148A publication Critical patent/FR1395148A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/26—Making other particular articles wheels or the like
    • B21D53/267—Making other particular articles wheels or the like blower wheels, i.e. wheels provided with fan elements

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
FR971256A 1963-04-16 1964-04-17 Manufacturing process of a bladed stator Expired FR1395148A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR971256A FR1395148A (en) 1963-04-16 1964-04-17 Manufacturing process of a bladed stator

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US273455A US3284881A (en) 1963-04-16 1963-04-16 Bladed stators
FR971256A FR1395148A (en) 1963-04-16 1964-04-17 Manufacturing process of a bladed stator

Publications (1)

Publication Number Publication Date
FR1395148A true FR1395148A (en) 1965-04-09

Family

ID=26207095

Family Applications (1)

Application Number Title Priority Date Filing Date
FR971256A Expired FR1395148A (en) 1963-04-16 1964-04-17 Manufacturing process of a bladed stator

Country Status (1)

Country Link
FR (1) FR1395148A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944328A1 (en) * 2009-04-08 2010-10-15 Snecma Stator part for e.g. turbojet engine of aircraft, has braze extended towards back on both sides of head of vane while being stopped in front of trailing edge of vane, where trailing edge is arranged in rear part of transversal perforation

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944328A1 (en) * 2009-04-08 2010-10-15 Snecma Stator part for e.g. turbojet engine of aircraft, has braze extended towards back on both sides of head of vane while being stopped in front of trailing edge of vane, where trailing edge is arranged in rear part of transversal perforation

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