摘要:
A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46).
摘要:
A gas turbine includes an annular combustion chamber and an outer wall of an annular combustion chamber. A straining ring is arranged on the outer wall of the annular combustion chamber and enables oscillations of the outer wall to be damped via friction. The effects of combustion oscillations produced by damaging vibrations of the annular combustion chamber are thus reduced. A method is further for damping an oscillation of an outer wall of an annular combustion chamber.
摘要:
The invention relates to a process for producing foamed polyolefin-based plastics blocks by first crosslinking a matrix comprising a) from 51 to 97% by weight of one or more polyolefins, selected from the group consisting of polyethylene and ethylene copolymer, b) from 3 to 20% by weight of a foaming agent, using &bgr;-radiation of energy >6 MeV. The thickness of the matrix is from 25 to 45 mm. The radiation dose is from 20 to 150 kJ/kg. During the irradiation, atmospheric oxygen is at least substantially prevented from reaching the surface of the matrix. After crosslinking, the crosslinked matrix is foamed by heating to a temperature >160° C. and decomposing the blowing agent.
摘要:
A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46).
摘要:
In a process known per se for producing base materials copper-clad on at least one side, in which a winding core carrying a copper foil is wound with a reinforcing fiber, the laid fibers are impregnated with a solvent-free resin and the resin is cured fully to reach the C-stage, it is proposed to use, as the resin, a solvent-free epoxy-isocyanurate resin having a viscosity at processing temperature of less than 1000 mPa.s and an NCO content of more than 20%.