MINIMIZING THE EFFECTS OF ICING IN THE INTAKES OF AEROSPACE PROPULSORS
Assignee
ROLLS-ROYCE PLC
Filed
Feb 17, 1989
Granted
Feb 4, 1992
Location
WARWICK EN GB
Abstract
An air intake suitable for an aerospace propulsor comprises a duct in which are provided two pirmary heat exchangers arranged in parallel relationship and a secondary heat exchanger downstream of the primary heat exchangers. The primary and secondary heat exchangers are arranged to place a cryogenic fluid in heat exchange relationship with the air flow through the duct. Icing of the primary heat exchangers is controlled by interrupting the flow of cryogenic fluid to each of the primary heat exchanger in turn. Thus while one heat exchanger is subject to ice accretion hereon, the temperature of the other increases sufficiently for de-icing thereof to occur.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 23, 1989
Rescinded
Aug 2, 1991
Duration
2 years, 2 months
Inventor
- 1JOHN L. SCOTT-SCOTT
Record Details
- Patent number
- US 5085037
- Application
- 07314702
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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