Patent
System for cooling the impeller of a centrifugal compressor
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TLDR
In this paper, a system for cooling the impeller of a centrifugal compressor in a turbomachine is described, which includes an end-piece that extends downstream and along with an annular metal sheet.Abstract:
A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstream side by an annular metal sheet. The sheet delimits, with the impeller of the compressor, a first annular passageway to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway to carry away a portion of the air flow coming out of the diffuser.read more
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Turbine cooling air from a centrifugal compressor
Marcus Joseph Ottaviano,Robert John Parks,John Lawrence Noon,Mark Michael D'andrea,Thomas Michael Regan +4 more
TL;DR: A gas turbine engine turbine cooling system as mentioned in this paper includes an impeller (32) and a diffuser (42), a bleed for bleeding clean cooling air (97) from downstream of the diffuser, and one or more channels (150) in fluid communication with the bleed.
Patent
Gas turbine engine buffer cooling system
Gabriel L. Suciu,Ioannis Alvanos +1 more
TL;DR: A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly as mentioned in this paper.
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Centrifugal compressor forward thrust and turbine cooling apparatus
Marcus Joseph Ottaviano,Robert John Parks,John Lawrence Noon,Mark Michael D'andrea,Thomas Michael Regan,Aaron Todd Williams +5 more
TL;DR: A gas turbine engine centrifugal compressor axial forward thrust apparatus bleeds impeller tip aft bleed flow from between an annular centrifugal compressors impeller of a high pressure rotor and a diffuser directly downstream of the impeller.
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Buffer cooling system providing gas turbine engine architecture cooling
TL;DR: In this article, a gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passagway and a third passageways.
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Ventilation for a turbine wheel in a turbine engine
Stephane Pierre Guillaume Blanchard,Patrick Claude Pasquis,Wilfried Lionel Schweblen,Jean-Claude Christian Taillant +3 more
TL;DR: In this paper, a turbine engine, including a final centrifugal compressor stage associated with a diffuser for supplying air to a combustion chamber, and a ventilation element for ventilating a high-pressure turbine wheel, is disclosed.
References
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Patent
Gas turbine engine cooling supply circuit
TL;DR: In this paper, a turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine.
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TL;DR: In this paper, a cooling airflow modulation system for use on gas turbine engines is presented. The system utilizes one or more circumferential manifolds for collecting and providing a source of high-pressure cooling air to hot turbine parts.
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