Abstract:
THE FRICTION WELDER HAS A FLOATING SHROUD IN THE TAIL STOCK THAT PROVIDES RADIAL SUPPORT OF A WORKPIECE HAVING THIN OR FRAGILE PORTIONS. THERE IS LIMITED SHROUD ROTATION RELATIVE TO THE TAIL STOCK DURING THE WELDING PROCESS SO THAT TORSIONAL FORCES GENERATED DURING FRICTION WELDING WILL NOT BE TRANSMITTED FROM THE WORKPIECES THROUGH THE SHROUD TO THE TAIL STOCK. THIS ALLOWS THE WORKPIECES TO BE JOINED WITHOUT DESTRUCTION OR DAMAGE BY THE FRICTION WELDING PROCESS. THE SHROUD HAS A PLURALITY OF SEGMENTS
FACILITATING EASY REMOVAL OF THE WORKPIECES FROM THE TAIL STOCK.
Abstract:
A METHOD OF JOINING TWO TUBE PANELS EACH INCLUDING PARALLEL, LATERALLY ADJACENT TUBES HAVING THEIR INTERTUBE SPACES CLOSED BY METALLIC WEBS COMPRISING, PROVIDING AT ONE END OF ONE OF THE TUBE PANELS NOTCHES IN THE WEBS EXTENDING TO THE ASSOCIATED TUBE ENDS, POSITIONING THE NOTCHED END OF THE PANEL IN ABUTTING PLANAR RELATIONSHIP WITH THE SECOND PANEL SO THAT CORRESPONDING TUBES OF THE PANELS ARE IN COAXIAL RELATION AND CORRESPONDING WEBS ARE IN OPPOSING RELATION TO FORM ACCESS OPENINGS FOR CIRCUMFERENTIAL WELDING OF THE ABUTTING TUBE ENDS, WELDING THE ABUTTING TUBE ENDS TOGETHER CIRCUMFERENTIALLY ABOUT THE JUNCTION OF THE ABUTTING TUBES, AND SEAL WELDING THE ENDS OF THE CORRESPONDING WEBS TO ONE ANOTHER INCLUDING CLOSING THE ACCESS OPENINGS WITH A METALLIC FILLER MATERIAL.
Abstract translation:1329423熔融焊接BABCOCK&WILCOX CO 18 Nov 1970 [18 Nov 1969] 54737/70标题B3R [也在F4部分]气密管壁包括两个初始分离的板10,12,其具有倾斜的管端22和切口18 腹板16,其在面板10,12处于邻接关系时提供圆周管焊接通路。 如果腹板16较宽,则在每个管端附近设置单独的切口。 在一个修改中,仅在一个面板10,12中提供更大的凹口。由切口18提供的进入凹槽通过焊接金属或焊接的插入板填充。 圆周管焊接可以通过两个电弧通过实现,第一个电弧通过,其中第一个使用氦气,并且可以由两个焊工在壁的每一侧上一个实现。
Abstract:
A method of repairing a turbine rotor wheel having a damaged dovetail includes removing the damaged dovetail from the turbine wheel, leaving a turbine wheel body and welding a ring about the turbine wheel body in place of the removed damaged dovetail. During the welding process, including during preheating, welding or stress relieving, the temperature of the wheel body and ring is differentially controlled to introduce residual stresses in the ring. After welding a dovetail is formed in the ring for receiving turbine bucket dovetails. As a result, the ring has residual compressive stresses in a cold condition of the turbine whereby reduced net stresses in the ring in the location of the new dovetail during hot turbine operating conditions are reduced.
Abstract:
A method of making a BLISK by linear friction welding, comprises providing a stub on the circumferential surface of a turbine disk and defining a weld joint surface on the radially outermost face of the stub. The weld joint surface follows the annulus curvature in axial and circumferential directions while remaining flat in a third direction. A blade is applied radially to the stub and linear friction welding of the blade to the stub is effected by oscillating the blade in said third direction while applying a welding force inwardly along the blade.
Abstract:
Provided are a gas turbine multi-hole film-cooled combustor liner, which can be manufactured with improved accuracy in shape and position of cooling holes in a very short time, ensuring desirable buckling strength and satisfactory cooling performance. A planar flat member is curved to form a liner shell of a cylindrical shape, the cylindrical member is welded in the longitudinal direction thereof to form a cylindrical shell. Then a wavy configuration and a corrugated configuration are formed on the cylindrical shell by a hydro-bulging method, cooling holes are formed through the liner shell by laser drilling at or near wave crest portions of the wavy configuration of the liner shell, and inner rings are attached to the liner shell by resistance spot welding or vacuum brazing.
Abstract:
The invention is a method for repairing a protectively coated, locally damaged turbomachinery vane without removing the vane from its parent turbomachinery module. The method includes applying a diffusible coating precursor to the damaged region of the vane and diffusing the coating precursor into the vane in the presence of a nonreactive atmosphere. The nonreactive atmosphere is confined to a chamber that contains the damaged vane, the chamber being bounded in part by the turbomachinery module itself. A conventional stress relief machine is used to heat only the damaged region of the vane to a temperature sufficient to promote diffusion of the precursor into the vane. The method uses equipment and supplies that are routinely available or easily fabricated from common, inexpensive materials. Use of the method avoids the expense and delay of removing the vane from its parent module.
Abstract:
A method of brazing which includes deposition of brazing material by electrophoresis. Deposition is performed with a low viscosity, low surface tension bath comprising an alcohol, a nitroalkane, and a complex ionic solute. Brazing powder is added to this bath in the quantity of about 0.02 to about 0.04 kilograms per liter. A nonconductive coating is applied to areas where a brazing material should not be deposited, such as small passageways. This method is shown to be useful in applying brazing material adjacent small passageways, such that the brazing material is accurately deposited and does not flow into and interfere with the passageway after the braze joint is formed.