31results about How to "Reduce metal temperature" patented technology

An engine cylinder head has an exhaust manifold cast in the cylinder head. A turbocharger with a turbine body is adapted to mount directly to an exhaust outlet mounting face of the exhaust manifold. A dual level water jacket within the cylinder head has separate coolant feeds for upper and lower cooling jackets. The cooling jackets extend above and below the exhaust outlet and are connected inward of the exhaust mounting face to reduce metal temperatures of the mounting face below those of the turbocharger exhaust inlet flange. Separate cores for the upper and lower jackets are connected at coolant inlet and outlet locations at opposite ends. Intermediate core print connectors form controlled flow passages between the upper and lower jackets and exhaust ports in the cylinder head and integrated manifold. The improved cooling in these areas lowers operating temperatures in the cylinder head and obviates the need for a separate exhaust manifold.

A turbine blade having an internal cooling system with dual serpentine cooling channels in communication with tip cooling channels is disclosed. In at least one embodiment, the cooling system may include first and second tip cooling channels in communication with the first and second serpentine cooling channels, respectively. The first tip cooling channel may extend from the leading edge to the trailing edge and be formed from a first suction side tip cooling channel and a first pressure side tip cooling channel. The second tip cooling channel may extend from a midchord region toward the trailing edge and may be positioned between the pressure and suction sides such that the second tip cooling channel is positioned generally between the first suction side and pressure side tip cooling channels. The first and second tip cooling channels may exhaust cooling fluids through the trailing edge.

A turbine airfoil having walls with radial extending near wall cooled vortex flowing channels to provide for a high cooling effectiveness with a low cooling flow requirement. A thermal skin is bonded over a main spar in which skewed ribs extend from both the spar and the thermal skin to form a vortex flowing path along the radial channels. The vortex flowing radial channels can be single pass radial channels or connected to form a 3-pass serpentine flow circuit with tip holes to discharge the cooling air from the radial channels and cool the blade tip periphery.

A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the airfoil portion. The at least one cooling circuit has at least one passageway extending between the root and the tip. The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity.

A cooling system for a turbine airfoil of a turbine engine has a multiple suction side cooling slots extending from a front edge on the suction side to the center of the trailing edge or even to the pressure side of the center line and a pressure side cooling slot curving to a pressure side outlet forward of the trailing edge and having a front pressure side lip that is aligned with or forward of the front edge of the suction side cooling slots. The suction side cooling slots receive cooling flow from the pressure side cooling slots through a boundary layer bleed valve, which is also aligned with or rearward of the pressure side lip. The cooling system may also combine double impingement cooling with these features. The cooling system minimizes shear mixing, reduces hot spots and can reduce the trailing edge thickness, resulting in more efficient stage performance and extended operational life.

A method for hybrid wafer-to-wafer bonding, comprising: providing two silicon wafers with Cu pattern structures, a conventional Cu BEOL process is adopted on the silicon wafers to obtain the planarized surface with copper and dielectric; removing part of the Cu on the planarized surface of the Cu pattern structures by adopting an etching process to form a certain amount of Cu recesses; depositing a layer of bonding metal on the surface of the Cu by adopting a selective deposition process; performing surface activation on the bonding metal and the dielectric by adopting a surface activation process; aligning and pressing the two silicon wafers together to obtain the dielectric bonding; and obtaining the metal bonding through the annealing process. The sufficient metal bonding can be obtained at low annealing temperature according to the present invent, thereby the risk of dielectric delaminating caused by thermal expansion mismatch is reduced, which is conducive to reduce the difficulty of process integration, save process time and improve product yield.

Method for assembling into turbine sets turbine components having internal cooling passages. The turbine components are classified according to flow capability through the internal cooling passages and turbine sets are assembled in which the turbine components have the same flow capability classification.

A radiant superheater arranged to hang at the upper portion of a furnace of a boiler. The radiant superheater is substantially planar and includes a first vertical pass, a first connection pass, a second vertical pass, a third vertical pass, a second connection pass, and a fourth vertical pass. Each vertical pass includes an upper end and a lower end. The vertical passes are connected in series, so that steam to be superheated enters at the upper end of the first vertical pass and flows through the first vertical pass and from the lower end of the first vertical pass via the first connection pass to the lower end of the second vertical pass and through the second vertical pass and from the upper end of the second vertical pass to the upper end of the third vertical pass and through the third vertical pass and from the lower end of the third vertical pass via the second connection pass to the lower end of the fourth vertical pass and through the fourth vertical pass, to be discharged from the upper end of the fourth vertical pass. The first connection pass is arranged below the second connection pass so as to shield the second connection pass from radiation from the lower portion of the furnace.

A method includes providing a furnace including a radiant heating zone having metal heating coils and burners, concurrently applying a combustion media, having a combustibility, and a diluent to the burners, the burners burning the combustion media producing flames heating the radiant heating zone, and the diluent reducing the combustibility of the combustion media for reducing heat generated by the flames for reducing heat degradation of the metal heating coils.

The invention discloses a gas turbine combustor transition section with a cooling structure, and belongs to the technical field of a gas turbine. The outer surface of a transition section body is provided with a plurality of cooling components; each cooling component comprises a connecting piece and a heat dissipation part; the cooling components are distributed in an array, and every two adjacent cooling members are distributed in a staggered manner; each heat dissipation part is in the shape of a bowl or is spiral or dendritic or is in other shapes that not only can surface area be increased but also flow resistance is smaller. According to the gas turbine combustor transition section disclosed by the invention, the temperature of the transition section can be lowered and the service life of the transition section can be prolonged by increasing the heat exchange area of the outer surface of the transition section; meanwhile, the integrity of the transition section body cannot be broken, the reliability of a thermal barrier coating cannot be influenced and the thermal insulation effect of the can be helped to be enhanced by the cooling structure; pressure loss brought by the cooling structure is low, so that the efficiency of the gas turbine can be helped to be improved.

A receiver with a configuration of saturated and superheated steam solar modules in a tower solar concentration power plant. The configuration allows the incidence of radiation on both sides of the superheated steam module, providing significant benefits for its durability and global control of the power plant.

The invention discloses a turbine guide vane and a gas turbine engine. A cooling cavity is arranged in the turbine guide vane; the turbine guide vane comprises a front edge, a tail edge, a pressure surface and a suction surface; premixed gas injection holes communicating with the cooling cavity are formed in the turbine guide vane; and fuel is injected to the inner wall face of the cooling cavity from the cooling cavity, so that the fuel absorbs heat and is gasified on the inner wall face of the cooling cavity and then mixed with cold air in the cooling cavity to form premixed gas, and the premixed gas is injected to high-temperature high-pressure fuel gas around the turbine guide vane via the premixed gas injection holes to be combusted. According to the turbine guide vane, the energy added by the fuel combustion is increased through the supplementary combustion in the turbine guide vane, so that the temperature margin of a subsequent stage of turbine is fully utilized, the output power of the whole machine is greatly increased, and the power-to-weight ratio of the gas turbine engine is increased.