Accession Number : ADD012003

Title :   One-Piece HPTR Blade Squealer Tip.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Horvath,Richard L

Report Date : 10 Sep 1985

Pagination or Media Count : 4

Abstract : An improved high pressure turbine rotor blade and tip cap structure therefor is provided which comprises a tip end closure for the blade bonded to the end wall of the blade casting and including a base plate member and a pair of upstanding side walls defining a peripheral contour coincidental with and faired to the cambered side walls of the casting, the base plate member having a plurality of radially outwardly opening passageways therethrough and disposed along the chord of the blade and communicating with a channel included in the radially outwardly facing surface of the casting along a chord of the blade, the passageways disposed along axes at angles to the base plate whereby coolant fluid flowing therethrough is directed against the tip side wall surfaces; and opening is provided through the end wall of the casting in the form of a slit or a plurality of holes along the chord of the blade and intersecting the channel, to define an outlet through the end wall for passage of coolant fluid through the blade. (Author)

Descriptors :   *PATENTS, *ROTOR BLADES, *CASTINGS, CAPPING, CLOSURES, GAS TURBINE BLADES, BONDING, FAIRINGS, HOLES(OPENINGS), COOLANTS, AIR COOLED, HIGH PRESSURE, GAS TURBINE ROTORS, CASTING

Subject Categories : Mfg & Industrial Eng & Control of Product Sys
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE