Patent
Rotor assembly having a multistage disk
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TLDR
In this paper, a rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is described, and various construction details which enhance axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed.Abstract:
A lightweight, rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is disclosed. Various construction details which enhance the axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed. The rotor assembly employs a frustoconical member to connect a shaft to the disk.read more
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Patent
Turbine support assembly including turbine heat shield and bolt retainer assembly
Steve Robert Fledderjohn,James Charles Przytulski,Sidney Baker Elston,Alan Raymond Gilchrist,Ambrose Andreas Hauser +4 more
TL;DR: In this article, an annular integral bolt heat shield and axial retention apparatus are provided to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules.
Patent
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Patent
Non-parallel spacer for improved rotor group balance
TL;DR: In this article, a non-parallel spacer is used to compensate for rotor bow and the associated imbalance of the rotor group, which can be achieved without disassembly of rotor group and clocking of its individual components.
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Patent
Turbofan engine lubrication means
TL;DR: A turbofan engine is provided with a compressor and a turbine, all of the bladed stages of the turbine being rotor stages as discussed by the authors, and the rotor stages within the compressor and the turbine are relatively counterrotating.
Patent
Turbine engine with integral compressor and alternator rotor
TL;DR: In this paper, a gas turbine engine with an armature rotor integrally mounted on the forward end of the compressor shaft and driven by a locknut for the forward main bearing is described.
Patent
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TL;DR: In this paper, the rotor of a single-shaft gas turbine with compressor and turbine stages is constructed, and the intermediate members are axially divided shells surrounding the connecting rod and at least one clamping ring clamping the shells together and bracing them against the outer periphery of the connecting rods.
Patent
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Patent
Gas turbine engine axial flow multistage compressor
TL;DR: In this article, a gas turbine engine axial flow multistage compressor having a rotor member and a plurality of platform elements, each of which has rotor blade members mounted thereon and each is itself disposed radially outwardly of and spaced from the rotor member, is described.