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A common arrangement for low pressure air powered boosters is for the booster pistons to be direct coupled with the drive piston, on the same centreline. The low pressure cylinder has a considerably larger section area than the high pressure cylinders, in proportion to the pressure ratio between the drive and boosted gas.
Schematic diagram illustrating a 2-spool, low-bypass turbofan engine with a mixed exhaust, showing the low-pressure (green) and high-pressure (purple) spools. The fan (and booster stages) are driven by the low-pressure turbine, whereas the high-pressure compressor is powered by the high-pressure turbine.
A small stationary high pressure breathing air compressor for filling scuba cylinders A powerful compressor for street work. Model XASS from Atlas Copco circa 1985. Natural gas compressor at a gas well High pressure reciprocating compressor from Belliss and Morcom, used in the bottling industry
It uses a similar two-spool configuration to the LEAP-1C, with a one-stage fan, three-stage booster, 10-stage high-pressure compressor, two-stage high-pressure turbine and six-stage low pressure turbine (although the LEAP-1C has seven low pressure stages).
GE produces the high-pressure compressor, combustor, and high-pressure turbine, Safran manufactures the fan, gearbox, exhaust and the low-pressure turbine, and some components are made by Avio of Italy and Honeywell from the US. Both companies have their own final assembly line, GE in Evendale, Ohio, and Safran in Villaroche, France.
At high overall pressure ratios, the compression system is usually split into two units; a low-pressure (LP) compressor mounted on one shaft followed by a high-pressure (HP) compressor mounted on the HP shaft and driven by its own (HP) turbine. On civil turbofans, the first stage of the LP compressor is often a single-stage fan.
Although in isolation centrifugal compressors are capable of running at quite high pressure ratios (e.g. 10:1), impeller stress considerations limit the pressure ratio that can be employed in high overall pressure ratio engine cycles. Increasing overall pressure ratio implies raising the high-pressure compressor exit temperature.
The compressor is designed with 3D aerodynamics and its first five stages are blisks, combined bladed-disk. The combustor is lean burning for greater efficiency and 30% NOx margin to CAEP/8. The compressor and high pressure turbine are made from powdered metal.
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