single-stage turbine

It had an annular combustion chamber with 24 nozzles and a single-stage turbine.

The HP compressor is driven by a single-stage turbine.

The J35 was fairly simple, consisting of an eleven-stage axial-flow compressor and a single-stage turbine.

The engine has a seven-stage compressor, annular combustion chambers, and a single-stage turbine.

The Dovern was the next design, featuring a nine-stage axial compressor and single-stage turbine.

The HP spool has 4 axial compressor stages and 1 centrifugal stage, driven by a single-stage turbine.

The combustion area consisted of twenty steel flame cans arranged in a "canular" layout, exiting into the single-stage turbine.

Overall the engine had a five-stage compressor providing air at a compression ratio of 3:1 to ten flame cans, which powered a single-stage turbine.

The single-stage turbine engine drove a single propeller, which had a tendency to develop unbalanced torque and thus to roll in the water, affecting its accuracy.

The LP and HP compressors both had 7 stages and were each driven by a single-stage turbine.

RD-500 was a close copy of the Derwent with a single-stage centrifugal compressor, nine combustion chambers and a single-stage turbine.

A single-stage turbine drives the 10 stage all-axial compressor, whilst a two-stage free power turbine drives the load.

Coppus single-stage turbines meet the latest requirements of API-611 Third Edition for the oil refinery and chemical industries, without exception.

The engine is called the TJT 2500 and is a single-stage turbine, using a centrifugal compressor and axial turbine.

A simple and robust unit with six-stage compressor, annular combustor, and single-stage turbine, it initially gave 1,200 pounds of thrust but improved to 1,600 in production versions.

To achieve this, the initial design used a low-pressure (LP) axial compressor and a high-pressure (HP) centrifugal compressor, each being driven by its own single-stage turbine.

The first engine, its development designation being BOl.1 (Bristol Olympus 1), had six LP compressor stages and eight HP stages, each driven by a single-stage turbine.

The air then flows into a single-stage centrifugal compressor, through the annular reverse-flow combustion chamber, and finally through a single-stage turbine that powers the compressors at about 45,000 rpm.

At about this time Frank Whittle wrote his thesis on turbine engines, using a centrifugal compressor and single-stage turbine, the leftover power in the exhaust being used to power the aircraft directly.

The SaM146 utilizes a single-stage turbine and as a new design has been developed to meet current and projected environmental standards, including regulations of the ICAO Committee of Aviation Environmental Protection Sixth Session (CAEP VI), set to become effective in 2008.