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Subsonic/Supersonic Ducts Modern Navy aircraft capable of supersonic flight pose another problem to aircraft designers because the airframe can withstand supersonic velocity air, but the engine cannot. There are two methods commonly used to diffuse the intake air and slow its flow to subsonic speeds during supersonic flight. One is to create a shock wave in the intake airstream, which will disrupt the flow and cause a decrease in velocity. The other method is to vary the area, or geometry, of the intake duct. The F/A 18 A-D uses the airframe intake ducting as a fixed opening/channel to the engine inlet and the air is slowed down during supersonic flight due to the divergent design and a ‘Vortex Generator” located in the inlet, or incorporating movable ramps as shown in Figure 1-15, view C, to change the area and shape of the intake duct. COMPRESSOR SECTION The primary function of the compressor is to supply air in enough quantity to satisfy the requirements of the combustion burners. Specifically, the compressor increases the air mass received from the air inlet duct and directs it to the burners in the quantity and at the pressures required. A secondary function is to supply compressor bleed air for various purposes in the engine and aircraft. The compressor provides space for mounting accessories and engine parts. There are two basic types of compressors. The compressor type is also the engine type, so a centrifugal-flow compressor is in a centrifugal engine. Centrifugal-flow compressors have a compression ratio of 5:1. Present-day axial flow compressors have compression ratios approaching 15:1 and airflows up to 350 lb. The addition of a fan raises these values to 25:1 and 1,000 lb. /sec. Centrifugal-Flow Compressors The single entry centrifugal-flow compressor (Figure 1-16) consists of an impeller (rotor element), a diffuser (stator element), and a manifold. The impeller picks up and accelerates air outward to the diffuser. The diffuser directs air into the manifold. The manifold distributes air into the combustion section. Double entry centrifugal-flow compressors (Figure 1-17) handle the same airflow with a smaller diameter. Small multi-stage centrifugal-flow engines used in aircraft (Figure 1-18), or as Auxiliary Power Units (APUs) that take advantage of this feature. Figure 1-16 — Elements of the centrifugal compressor. 1-12 Figure 1-17— Double entry centrifugal- flow compressor.PDF Image | JET ENGINE THEORY AND DESIGN
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