Abstract: A transpiration air cooled combustor for use with gas turbine engines includes an annular wall of laminated readily deformable metal having plural layers of diffusion bonded material in a combustor wall with inner and outer surfaces; each of the inner and outer surfaces has pores formed therein by a process such as photoetching to provide numerous inlets on the outer surface of the combustor wall for directing cooling air through the wall to a plurality of outlets in the inner surface for flow of cooling air across the inner surface; and wherein at least two surfaces of the layers includes a plurality of continuously formed curvilinear grooves communicating with the inlets and outlets and also intersecting one another to form crossover passages between the grooves for communicating the inlets and outlets and wherein the curved grooves serve to produce minimal surface distortion and stretch marks across curvilinear portions of the outer wall portion of the combustor assembly to prevent formation tears therein

Abstract: A transpiration air cooled combustor assembly for a gas turbine engine includes an annular liner of laminated metal with an inner sheet and an outer sheet having a plurality of mechanically formed holes therein on either side of a mechanically pressed waffle patterned core sheet with offset depressings and dimples on either face thereof; the dimples have raised lands bonded to the inner and outer sheets; small cross passages are drilled in the core sheet so that the margins of the cross passages are located in spaced relationship to the land surfaces thereby to prevent burr formation disruption of the bond joints; the core sheet has a total metal mass equivalent to the orginal metal mass prior to press displacement of metal to form the depressions and dimples therein except for the metal removed by formation of the cross passages which communicate offset depressions on opposite sides of the core sheet to form a tortuous intercommunicating flow path through said annular liner between holes in the inner and out

Abstract: A method for manufacturing a composite sheet of material having a controlled porous characteristic and made up of two or more metal lamina bonded together, including the steps of forming first and second sheets of porous material with a first and second array of openings therein offset with respect to one another; stacking the first and second sheets together to form a peripheral joint line therebetween having end edges indexed to align the first and second array of openings to form a coolant flow pattern through the stacked sheets; welding indexed end edges to fixedly connect the first and second sheets together; stretch-forming the stacked sheets by bending them under tension across a predetermined curvature on a form die to cause the first and second sheets to exceed their yield point to effect an intimate fit across juxtaposed surfaces thereon; thereafter further bending and restraining the welded end edges of the first and second sheets to produce a bond pressure between the sheets at the juxtaposed surf

Abstract: A method of bonding a laminated porous sheath to a cast strut includes the step of performing a compressible pad to have a plurality of closely spaced grooves on one surface thereon and a plurality of spaced apart lands on the opposite face thereof; locating a preformed porous laminate sheath over the outer surface of a cast strut and laser welding it thereto and thereafter assembling the preformed compressible pad to locate the plurality of grooves thereon in overlying relationship to a plurality of airflow openings in the porous laminated sheath and with ribs on either side of the grooves being located in juxtaposed relationship with the outer surface of the porous laminated sheath for uniformly distributing a load thereto; locating the preassembled casting, sheath and compressible pad within a contoured opening formed by a three piece pressure block fixture and applying a predetermined pressure to the assembled parts while subjecting them to a predetermined bond temperature while applying a vacuum.

Abstract: A porous seal element usable as a blade tip seal in a turbomachine or as an element of a labyrinth seal is made up of a large number of strips disposed edgewise to the sealing face of the element and extending in the direction of relative movement of the seal elements. The strips have grooves extending across the strip for discharge of a cooling fluid such as air. The presence of the grooves provides a low density structure at the seal face of the seal element which may be abraded if there is rubbing contact and provides for metering of coolant at the rear face of the seal element. The seal element is fabricated by etching sheets so each sheet defines a number of parallel strips joined by weak ties and with the grooves extending across the strips; stacking the sheets and bonding them together; and then separating the bonded structure at the weak ties so that each stack of strips defines a seal element.

Abstract: A porous seal element usable as a blade tip seal in a turbomachine or as an element of a labyrinth seal is made up of a large number of strips disposed edgewise to the sealing face of the element and extending in the direction of relative movement of the seal elements. The strips have grooves extending across the strip for discharge of a cooling fluid such as air. The presence of the grooves provides a low density structure at the seal face of the seal element which may be abraded if there is rubbing contact and provides for metering of coolant at the rear face of the seal element. The seal element is fabricated by etching sheets so each sheet defines a number of parallel strips joined by weak ties and with the grooves extending across the strips; stacking the sheets and bonding them together; and then separating the bonded structure at the weak ties so that each stack of strips defines a seal element.