Abstract: A monolithic inkjet printhead formed using integrated circuit techniques is described. A silicon substrate has formed on its top surface a thin polysilicon layer in the area in which a trench is to be later formed in the substrate. The edges of the polysilicon layer align with the intended placement of ink feed holes leading into ink ejection chambers. Thin film layers, including a resistive layer, are formed on the top surface of the silicon substrate and over the polysilicon layer. An orifice layer is formed on the top surface of the thin film layers to define the nozzles and ink ejection chambers. A trench mask is formed on the bottom surface of the substrate. A trench is etched (using, for example, TMAH) through the exposed bottom surface of the substrate and to the polysilicon layer. The etching of the polysilicon layer exposes fast etch planes of the silicon. The TMAH then rapidly etches the silicon substrate along the etch planes, thus aligning the edges of the trench with the polysilicon.

Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The combustor includes an air swirler, and the one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends circumferentially through the deflector portion for receiving cooling fluid therein. Because the deflector-flare cone assembly receives pre-loaded braze tape and braze rope, a single braze operation secures the deflector-flare cone assembly within the combustor and to a combustor air swirler.

Abstract: A method of fabricating an annular liner for a combustion chamber of a gas turbine engine. The combustion chamber has a dome including a fuel nozzle for delivering fuel to the combustion chamber. A metal piece is formed into an annular section constituting at least a portion of the liner and having at least one seam extending generally axially with respect to an axial centerline of the liner. An upstream end of the liner is machined to have a registration feature for connecting the liner to the combustion chamber dome in at least one predetermined orientation with respect to the dome. Further, the method includes ensuring the registration feature and the seam are located relative to each other on the liner so the seam is at a preselected position with respect to the combustion chamber dome when the liner is connected to the combustion chamber dome in the predetermined orientation.

Abstract: A multinozzle ink jet recording device having a dense arrangement and a method of producing the same are disclosed. Two electrodes for applying a voltage to the side walls of a piezoelectric plate lie in the range of a pressure chamber, so that an electric field is prevented from acting on portions which do not contribute to the ejection of an ink drop. This obviates the waste of voltage and thereby realizes low voltage drive which reduce the size of the pressure chamber. All the grooves serve as pressure chambers without any slit or similar wasteful space intervening between them. Thus the multinozzle print head has a dense configuration. With such a print head, the recording device achieves a miniature and compact arrangement.

Abstract: A rocket engine has a combustion chamber, an injector, and an attachment between the combustion chamber and the injector. The attachment includes an annular metallic deposit joined to the chamber wall outer surface, and an annular transition ring structure. The transition ring structure has an annular step collar, and an annular adaptor ring brazed to the annular step collar. The adaptor ring is welded on one end to the injector and on the other end to the metallic deposit.

Abstract: A process for manufacturing components of gas turbine engine combustors, including the steps of performing a plurality of forming steps on a workpiece of a designated material to produce a combustor component of desired size and shape without exceeding a forming limit of the designated material, the forming steps being performed without any intermediate heat treatment on the workpiece.

Abstract: A rocket engine has a combustion chamber, an injector, and an attachment between the combustion chamber and the injector. The attachment includes an annular metallic deposit joined to the chamber wall outer surface, and an annular transition ring structure. The transition ring structure has an annular step collar, and an annular adaptor ring brazed to the annular step collar. The adaptor ring is welded on one end to the injector and on the other end to the metallic deposit.

Abstract: A method of forming an internal channel within an article, such as a cooling channel in an air-cooled blade, vane, shroud, combustor or duct of a gas turbine engine. The method generally entails forming a substrate to have a groove recessed in its surface. A sacrificial material is then deposited in the groove to form a filler that can be preferentially removed from the groove. A permanent layer is then deposited on the surface of the substrate and over the filler, after which the filler is removed from the groove to yield the desired channel in the substrate beneath the permanent layer.

Abstract: A gas generator is produced of separate units, including a mixing head, a casing and an outlet branch pipe, which are interjoined by welding. The mixing head is welded to the outlet branch pipe through a spacer and a structural spherical casing. The spacer and the outlet branch pipe are made of two inter-brazed envelopes, the inner envelopes of the spacer and the branch pipe are welded at their end faces by electron-beam welding, and the outer structural envelopes are welded by electron-arc welding using a split ring. The spacer is joined to the mixing head by automatic gas-shielded welding. The spherical casing of the gas generator is welded to the outlet branch pipe and the mixing head after the spacer is welded to the mixing head and the outlet branch pipe.

Abstract: A coating with the ability to protect (1) the inside wall (i.e., lining) of a rocket engine combustion chamber and (2) parts of other apparatuses that utilize or are exposed to combustive or high-temperature environments. The novelty of this invention lies in the manner a protective coating is embedded into the lining.

Abstract: An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its smaller end with a rocket body, and terminates at its larger end in a generally contact contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time.

Abstract: A rocket engine is fabricated by a multistep brazing and welding technique. An annular step collar is fns brazed to a trnnsition joint. This first subassembly is second brazed to the combustion chamber. This second subassembly is third brezed to an annular adaptor to form a third subassembly. The succeeding brazing steps are performed at successively lower temperatures. The third subassembly is welded to an injector.

Abstract: A method for forming an ink jet nozzle plate includes providing a structure having a top substrate layer, a bottom substrate layer, and a buried layer disposed between the top substrate layer and the bottom substrate layer; selectively etching the top substrate layer to form a plurality of spaced ink cavities in the top substrate layer exposing portions of the buried layer; removing by etching the bottom substrate layer and bonding a base having ink delivery channels over the top substrate layer, with at least one channel corresponding to each ink cavity to thereby form the ink jet nozzle plate; and providing a mask having a plurality of openings over the buried layer and etching through such mask openings through the buried layer to the ink cavities to provide at least one bore region corresponding to each ink cavity to provide ink ejection access to such ink cavities so that the buried layer has portions which overhang the ink cavity.

Abstract: A regenerative circuit structure is built up by implementing the following steps in particular: an intermediate layer is made on a support core representing the inner profile of the structure; a series of channels regularly distributed around the core is made with the channels opening to face the intermediate layer, each of the channels being provided with a soluble insert; the support core is preheated and the body of the structure is made by thermal spraying under a vacuum; channels are machined in the body from the outside, and said channels are filled by means of soluble inserts; a closure layer is formed to close the channels in the body, and an outer envelope is formed by thermal spraying under a vacuum, after preheating; and all of the soluble inserts and the intermediate layer are eliminated.

Abstract: A fabricating method for a one-piece refractory metal rocket engine chamber is described. Hollow liner sections of a platinum group metal or alloy are inserted into a chamber barrel portion to form the combustion chamber, connecting into a conical portion, a venturi throat and into a second conical portion, forming an expansion nozzle exit of the chamber. The hollow liner sections correspond to the interior shapes of the chamber portions. A refractory metal split hollow mandrel completes an assembly which is subjected to a hot isostatic pressing cycle. This HIP cycle expands the hollow mandrel, supporting the liner, outward against the chamber wall, pressure bonding the liner sections to the chamber portions. Scarfed edges of the liner sections are also bonded. The split mandrel is then chemically removed from the chamber resulting in a lined rocket engine chamber.

Abstract: Separate adhesive is avoided in the manufacture of a thermal ink jet printhead by positioning a thermoplastic nozzle plate (1) on a semiconductor circuit chip (3) and electrically firing the ink ejection resistors (5) in a controlled amount to melt the lower surface in contact with the chip while not damaging the body of the nozzle plate. The resistors are fired in their intended pattern of operation during use so not to damage the resistors. Additional resistors may be added just for this bonding operation if needed with particular chip designs.