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Unfortunately, during the initial engine design phase, significant uncertainty in one or more of the above requirement areas usually exists. There are two prevalent reasons for this uncertainty: 1. High System Complexity - Modem propulsion systems are becoming increasingly integrated with airframe systems. This tends to increase the complexity ofan already incredibly complex machine. Physical processes inherent in gas turbine engines such as compressible flow through a complex flowpath and combustion are still difficult to accurately model, although significant progress has been made over recent years. Increased airframe integration also increases the number and complexity of propulsion system interfaces. In the case where a new aircraft and engine are both developed, the aircraft development program normally lags behind the propulsion system development by 1-2 years. This is primarily due to the lengthy ground test development and qualification program required by the engine manufactures and customer/regulators such as the US Air Force or Federal Aviation Administration (FAA). This lag results in significant uncertainty in propulsion system interface definition early in the engine design cycle (engine detail design typically runs concurrent with aircraft preliminary design). 2. Desire for Increased System Capabilities - increased functional performance and safety levels while reducing weight and cost result in more iteration at higher levels of abstraction (i.e. at the major engine module level). It is the major engine module designs along with the design of the top-level engine control laws that set the requirements for control system hardware. As the major engine modules (e.g. fan, compressor, and exhaust nozzle) and control modes (e.g. closing loop on fan speed, calculated airflow, or engine pressure ratio) continue to iterate, so do the significant design requirements for the control system components. Hague's work in describing a gas turbine engine development process by using the Design Structure Matrix (DSM) clarifies this statement by showing the dependencies and 32PDF Image | Improving Gas Turbine Engine Control System
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