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GAS TURBINES IN SIMPLE CYCLE COMBINED CYCLE APPLICATIONS

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GAS TURBINES IN SIMPLE CYCLE COMBINED CYCLE APPLICATIONS ( gas-turbines-in-simple-cycle-combined-cycle-applications )

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Fig. 23. Stator case for the General Electric 179 engine. (Source: “Aircraft Gas Turbine Engine Technology” McGraw Hill) Therefore most gas turbine designs incorporate axial compressors. In newer designs, the compressor and turbine modules may be split into further submodules, to lessen the stress on individual components and achieve better efficiencies. So a compressor may have a low pressure (LP) module or LPC, and a high pressure module (HPC). In this case there will be equivalent high and low pressure turbine modules (LPT and HPT). The LPC and LPT will operate on one long shaft at the same speed. The HPC and HPT will operate on a shorter shaft that fits around and concentric to, the low pressure shaft, and at a higher speed than the low pressure module. See Figure 21. Some contemporary gas turbines have three modules, designated low, intermediate and high pressure, each with their own shaft. This modular concept allows for module replacement or exchange, if maintenance to a module is required, without taking the entire gas turbine out of service. Module component aerodynamic and thermodynamic basics Air inlet section A gas turbine takes in many multiples of what an equivalent size reciprocating engine can. The air inlet is generally a smooth, bell shaped, aluminum alloy duct. It leads air into the compressor with minimized turbulence. Typically, struts brace the outer shell of the front frame to minimize air flow vibration. An anti-icing system directs compressor air (at discharge or some pressure higher than atmospheric) that is bled off an appropriate compressor stage, into these struts. The temperature of this air prevents ice formation. Ice ingestion can and has destroyed many gas turbine engines. Compressor module The compressor is made up of rotating blades on discs and stationary vanes that direct the air to the next row of blades. The first stage compressor rotor blades accelerate the air towards their trailing edges and towards the first stage vanes. The first stage vanes slow the air down and direct it towards the second stage compressor rotor blades, and so on through the compressor rotor stages (each stage is one rotating stage and one stationary stage). 18

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