A heat exchanger for high velocity fluids comprises a first conduit through which a first fluid flows at a high velocity, a second conduit in heat exchange relationship with the first conduit for conducting a second fluid at a high velocity to be heated by the first fluid in the first conduit, the first and second conduits having a common thermally conductive wall, the common thermally conductive wall having a shape to impose a centrifugal force on the first and the second fluids flowing through the respective conduits.
A recuperative exhaust-gas heat exchanger for a gas turbine engine is provided which has a crossflow/counterflow matrix around which the hot turbine exhaust gas flows, a distributing tube for directing the air delivered by a compressor into the crossflow/counterflow matrix and a collecting tube which is arranged parallel to the distributing tube and is intended for discharging the compressor air, heated via the crossflow/counterflow matrix, to a consumer. End faces of the distributing and collecting tubes which are remote from the compressor and consumer are closed. The closed end face of the collecting tube is firmly connected axially and radially to the turbine casing.
A radial flow heat exchanger (20) having a plurality of first passages (24) for transporting a first fluid (25) and a plurality of second passages (26) for transporting a second fluid (27). The first and second passages are arranged in stacked, alternating relationship, are separated from one another by relatively thin plates (30) and (32), and surround a central axis (22). The thickness of the first and second passages are selected so that the first and second fluids, respectively, are transported with laminar flow through the passages. To enhance thermal energy transfer between first and second passages, the latter are arranged so each first passage is in thermal communication with an associated second passage along substantially its entire length, and vice versa with respect to the second passages. The heat exchangers may be stacked to achieve a modular heat exchange assembly (300). Certain heat exchangers in the assembly may be designed slightly differently than other heat exchangers to address changes in fluid properties during transport through the heat exchanger, so as to enhance overall thermal effectiveness of the assembly.
A recuperator for a gas turbine engine comprises a plurality of cells that are orientated in an annular array and attached to one another at only the radially inner edges thereof. Each cell comprises a high pressure plate having spaced integral ribs thereon defining a plurality of low temperature compressed air passages and a low pressure plate having a plurality of spaced ribs defining a plurality of high temperature exhaust gas passages.
A method of manufacturing a recuperator for a gas turbine engine comprises the steps of stamping a plurality of spaced integral ribs on a metal plate so as to define a plurality of high pressure channels, stamping a plurality of spaced integral ribs on a second metal plate so as to define a plurality of low pressure channels, joining said first and second metal plates to form a cell, and joining a plurality of said cells to one another.
A small gas turbine generator set comprising a rotating group and combustor contained within a circumferential recuperator. The rotating group comprises an alternator rotor on a common shaft with a turbine wheel and compressor impeller, supported by double acting complaint foil thrust bearings and a radial compliant foil bearing. The circumferential recuperator consists of a plurality of apertured boundary foils having embossments for structurally spacing the foils apart, arranged to provide the flow channels, manifolds, and structure to permit the existence of differential pressure between each surface of the foil. The circumferential recuperator is unitarily constructed surrounding the rotating group and combustor wherein the inflowing air is heated by the recuperator before entering the combustor. Due to the intercompatibility and modularity of the components, the air flow path associated with the compressor discharge and the turbine inlet is formed upon installation of the rotating group and the recuperator and by final assembly of the combustor unit which forms a final enclosure for the turbine inlet air. The configuration of the circumferential recuperator provides improvement in engine performance by improving heat transfer effectiveness and additionally acts to absorb sound as well as to safely insulate the surrounding environment should the rotating group fail and be centrifugally driven outside of its primary containment.
