THE ROVER GAS TURBINE
(printed Oct.1950)

The Rover gas turbine is being developed for general use in the range of 100 to 2OO horse power.
It is suitable for marine and transport work where a reasonably light-weight compact unit is required, but where the low fuel consumption of a diesel is not necessary or is out-weighed by the ability to burn almost any type of fuel.

Description of Engine.
The engine consists of the following components in the order of air flow:

Compressor
A single stage centrifugal compressor, similar to an aircraft engine supercharger, is used. This has a single-sided impeller and runs at a maximum speed of 40,000 r.p.m.

Combustion Chambers
Fuel is burnt in two combustion chambers similar to those used on an aircraft jet engine. This heats the air to the temperature required by the turbine.

Compressor Turbine
From the combustion chambers the hot gases pass to the compressor turbine. The turbine rotor is machined from a Nimonic 90 forging complete with blades and is used to drive the compressor impellor and all auxiliaries. It is not mechanically connected to the output shaft, which is driven by a separate turbine.

Power Turbine
Mounted behind the compressor turbine is the power turbine. This is similar to the compressor turbine hut has somewhat longer blades and runs at a maximum speed of 30,000 r.p.m.

Turbine Exhaust
From the power turbine the exhaust gases, after having their velocity somewhat reduced in a diffuser, flow to the exhaust.

Reduction Gear
The Output shaft is driven through a 7:1 reduction gear giving a maximum output shaft speed of something under 5,000 r.p.m. Ground single helical gears are used with oil jet lubrication and the power turbine is mounted on the end of the high speed pinion shaft.

Auxiliaries.
All auxiliaries are mounted on the end of the engine and driven from the compressor turbine. They are as follows:
Starter:
A normal car starter is used with a step-up gear of 3:1.
Generator:
A pulley is provided for generator drive, running at 6,000 r.p.m.
Oil Pump:
This is of the scar type arid supplies oil to all bearings and gears.
Fuel Pump:
The fuel pump on the auxiliary drive case supplies fuel to the two burners which arc controlled by a spill throttle control.

Engine Characteristics.
The use of a separate power turbine gives the engine exceptional flexibility, the static torque being about three times the full power, full speed running torque.
Control is entirely on the fuel flow, the amount of fuel fixing the compressor turbine speed and hence the power output, independently of the power turbine speed.

Weight and Size.
The engine weighs approximately four hundredweight complete and measures approximately 2ft. 6 in. wide, 2ft. 6in. high and 4ft. long.

Power Output.
Although designed for 200 HP., the engines are at present rated at 100 HP, continuous rating and 150 HP. full power. The specific fuel consumption is about 1.6 lbs/BHP/hr. at 100 HP. and 1.2 lbs/BHP/hr. at full power.
The engines as used at present are not fitted with a heat exchanger, although provision is made for the use of a heat exchanger. Development of the heat exchanger is proceeding satisfactorily and it is hoped, when this is fitted, to bring the specific fuel consumption down to something like 0.8 lbs/BHP/hr. at full load.

The 1953 T3 Rover Jet Turbine car