Patent · US Active

Evaporative cooling for an aircraft subsystem

US8656727B2 · kind B2 · utility

3Cited by
53References
13Claims
0Family size

Assignee

Inventors

Key dates

Filing dateApr 8, 2008
Grant dateFeb 25, 2014
Priority date—
Expiry dateAug 24, 2032

Classification

  • Technology area (CPC Y)Emerging Cross-Sectional Technologies
  • CPC primaryY02T50/50
  • WIPO fieldTransport
  • WIPO sectorMechanical engineering

Abstract

Apparatus, systems, and methods provide for the cooling of an aircraft subsystem. Coolant is routed through a heat-producing subsystem to absorb heat from the subsystem and to maintain the subsystem at a desired temperature. Bleed air from an aircraft engine is cooled, dehumidified, and routed to a cooling mechanism. In the cooling mechanism, a portion of the heated coolant is evaporated into the dehumidified bleed air, cooling the remaining coolant. The reduced-temperature coolant is routed back to the subsystem to absorb further heat. Humid air from the cooling mechanism and the dehumidifying mechanism is utilized by other aircraft subsystems.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.