An Object-Oriented Computer Code for Aircraft Engine Weight Estimation

Abstract

Reliable engine-weight estimation at the conceptual design stage is critical to the development of new aircraft engines. It helps to identify the best engine concept amongst several candidates. At NASA Glenn (GRC), the Weight Analysis of Turbine Engines (WATE) computer code, originally developed by Boeing Aircraft, has been used to estimate the engine weight of various conceptual engine designs. The code, written in FORTRAN, was originally developed for NASA in 1979. Since then, substantial improvements have been made to the code to improve the weight calculations for most of the engine components. Most recently, to improve the maintainability and extensibility of WATE, the FORTRAN code has been converted into an object-oriented version. The conversion was done within the NASA’s NPSS (Numerical Propulsion System Simulation) framework. This enables WATE to interact seamlessly with the thermodynamic cycle model which provides component flow data such as airflows, temperatures, and pressures, etc. that are required for sizing the components and weight calculations. The tighter integration between the NPSS and WATE would greatly enhance system-level analysis and optimization capabilities. It also would facilitate the enhancement of the WATE code for next-generation aircraft and space propulsion systems. In this paper, the architecture of the object-oriented WATE code (or WATE++) is described. Both the FORTRAN and object-oriented versions of the code are employed to compute the dimensions and weight of a 300-passenger aircraft engine (GE90 class). Both versions of the code produce essentially identical results as should be the case.

Initial Assessment of Open Rotor Propulsion Applied to an Advanced Single-Aisle Aircraft

“…Propulsion system modeling was performed using NPSS (Numerical Propulsion System Simulation) [9][10][11] for cycle analysis and performance and WATE (Weight Analysis of Turbine Engines) [12][13][14] for aeromechanical design and weight estimates. Estimates for NO X emission indices were obtained from an empirical correlation representing an advanced, low NO X combustor.…”

Analysis of Turbofan Design Options for an Advanced Single-Aisle Transport Aircraft

“…[7][8][9] Analysis of the aeromechanical characteristics and estimates of the engine weight (including fan gearbox if applicable) were performed with the WATE (Weight Analysis of Turbine Engines) code. [10][11][12] Estimates for engine NO X emission indices (grams of NO X emitted from the engine per kilogram of fuel consumed by the engine) were obtained from a correlation developed by NASA combustor technologists during the latter stages of NASA's Ultra-Efficient Engine Technology program.…”

DBD Plasma Actuators for Flow Control in Air Vehicles and Jet Engines-Simulation of Flight Conditions in Test Chambers by Density Matching

“…Aeromechanical analysis and estimates of engine and component weights were calculated using the Weight Analysis of Turbine Engines (WATE) code (Ref. 38), which also provides a flow path schematic of the engine. Generic engine models representing four different thrust classes were developed: 300-, 150-and 50-passenger (PAX) aircraft engines, and a military jet-fighter engine.…”