s and other gas turbine engines are often uprated by adding a zero-stage, sometimes written '0' stage, to the front of a compressor. At a given core size, adding a stage to the front of the compressor not only increases the cycle overall pressure ratio, but increases the coremass flow. A further uprating may be done by adding another stage in front of the previously-added zero stage, in which case the new one may be known as a zero-zero stage. A comparison with other ways of uprating an existing engine without drastically redesigning the engine shows for a particular case, e.g. the Rolls-Royce/SNECMA M45H, the thrust could have been increased by 25% with a zero-staged l-p compressor or 10% with either an improved HP turbine or with water injection. Zero-staging is also combined with other modifications to provide increased thrust or lower turbine temperature. It may be required for an existing aircraft weight increase, or for a new application, as shown by the following examples. A 15-stage Rolls-Royce Avonpowered the Lightning F.1. A zero-stage, together with a new turbine, was added for the Caravelle III. A zero-zero stage was added for the Caravelle VI. The 7-stage Snecma Atar D was used in the Mystere II. A zero-stage was added for the E and G used in the Vautour and Super Mystere B.2. A zero-zero stage, together with a 2-stage turbine was added for the Atar 8 and 9 used in the Mirage III. The Rolls-Royce/Snecma Olympus 593 started with a 6-stage LP compressor. As the Concorde increased in weight during the design phase the take-off thrust requirement increased. The engine was given a zero-stage to the compressor, a redesigned turbine and partial reheat. Examples of zero-staging for land-based gas turbines are the aeroderivative GE LM2500+ and the heavy-duty GE MS5002B. An alternative to zero-staging used by some OEMs is supercharging the compressor with a fan driven by an electric motor. Zero-staging is demonstrated by the following relationship: ' where: core mass flow = ' core size =' core total headpressure ratio = '
inverse of core total head temperature ratio = ' i.e. core entry total pressure = ' core entry total temperature = ' So basically, increasing ' increases . On the other hand, adding a stage to the rear of the compressor increases overall pressure ratio, and decreases core size, but has no effect on core flow. This option also needs a Turbine with a significantly smaller flow capacity to drive the compressor.
