Turbine engine with intercooler in bypass air passage
US6134880A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Dec 31, 1997 |
| Grant date | Oct 24, 2000 |
| Priority date | — |
| Expiry date | Dec 31, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A turbine engine (20) having bypass and core passages (30 and 40), a high pressure compressor (80) for compressing air in the core passage and an intercooler (120, 220) for cooling core air (42) in the core passage prior to discharge by the high pressure compressor. The intercooler includes a plurality of heat exchange elements (140) positioned in the bypass passage through which all or a portion of the core air is transported. Heat in the core air is transferred via the heat exchange elements to the relatively cool bypass air, thereby cooling the core air and heating the bypass air. The turbine engine may have a counterflow intercooler (120), a radial flow intercooler 220 or an intercooler of other configuration. The turbine engine may have a high pressure compressor with two sections (82 and 86), with core air transported to and from the intercooler between sections, or a single section high pressure compressor, with core air transported to and from the intercooler upstream of the high pressure compressor. The turbine engine may be of turbofan, turboshaft, turboprop or other design.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.