Correlation of gas turbine engine weights and dimensions

Gerend, R.; Roundhill, J.

doi:10.2514/6.1970-669

Cited by 9 publications

(7 citation statements)

References 1 publication

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“…Finishing the study of the 'whole engine based' preliminary weight estimation methods, the method by Gerend and Roundhill (15) was used to estimate the weight of the gas turbines included in the database. As presented in the previous section, this method uses a lot of parameters to perform the calculations, which are not publicly available for most of the engines.…”

Section: Methods Quantitative Analysismentioning

confidence: 99%

“…Table 1 provides an overview of the available 'single equation' methods and the input variables required by each one of them. The method developed by Gerend and Roundhill (15) in 1970 was one of the first complete and detailed studies on the preliminary estimation of gas turbine weight and dimensions. The method follows again the 'whole engine based' approach, using data from over 350 engines available within the public domain, manufactured or at the design stage, dated between 1940 and 1980.…”

Section: Wt(lbs)= 250 + 0ּ175 •Fn To (Lbf )mentioning

confidence: 99%

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Evaluation of aero gas turbine preliminary weight estimation methods

Lolis

Giannakakis

Sethi

et al. 2014

Aeronaut. j. (1968)

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The estimation of gas turbine engine weight during the preliminary or conceptual design phase is a key part of a Techno-economic Environmental Risk Analysis (TERA). Several methods that are available in the public domain are analysed and compared, in order to establish the physics driving them and their suitability for the weight estimation of modern gas turbine engines. Among the tested methods, only WATE managed to achieve acceptable accuracy for engine optimisation studies. This work demonstrates that the age and restrictions of existing 'whole engine based' methods, along with their dependency on old engine databases make them unsuitable for future and novel aero engines. A hybrid weight modelling approach is proposed as a solution permitting the creation of simple 'whole engine based' methods that do not depend on the availability of existing engine data, which are also subject to uncertainties and incoherencies.

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Section: Methods Quantitative Analysismentioning

confidence: 99%

Section: Wt(lbs)= 250 + 0ּ175 •Fn To (Lbf )mentioning

confidence: 99%

Evaluation of aero gas turbine preliminary weight estimation methods

Lolis

Giannakakis

Sethi

et al. 2014

Aeronaut. j. (1968)

View full text Add to dashboard Cite

show abstract

“…Even though a detailed turbomachinery design would allow a high fidelity weight prediction, the nature of the present study dictated the implementation of semiempirical weight and length prediction correlations that accelerated the iterative parametric analysis process. For this reason, a weight and length prediction model 31 has been implemented, using statistically derived correlations. This model takes into account the effect of bypass ratio, combustor outlet temperature, overall pressure ratio, air mass flow and the technology level, providing with weight and length predictions.…”

Section: Engine Mass Length and Diameter Prediction Toolsmentioning

confidence: 99%

“…This model takes into account the effect of bypass ratio, combustor outlet temperature, overall pressure ratio, air mass flow and the technology level, providing with weight and length predictions. Equation (3) includes the estimation of bare engine weight, as described in Gerend and Roundhill 31 In the above equation, total weight is calculated through a reference ratio of engine mass to air mass flow, MT/M o , multiplied by actual air mass flow, M o , and several statistically derived corrections. These correction coefficients represent the whole engine (KENG), the engine core (KHP), and the fan (KW o ), while coefficient KGG represents the ratio of core to total mass.…”

Section: Engine Mass Length and Diameter Prediction Toolsmentioning

confidence: 99%

Effect of jet noise reduction on gas turbine engine efficiency

Doulgeris

Korakianitis

Avital

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article introduces a method for gas-turbine preliminary design, featuring jet-noise reduction as one of the main design objectives, or as the main objective. Selected methods have been implemented in an integrated systemic approach tool that includes gas turbine performance, aircraft performance and noise prediction. This tool enables the optimisation of the thermodynamic cycle for low noise, low fuel consumption, or a compromise between the two. Two case studies have been carried out for a 4000 nautical mile, 216-passenger aircraft: one targeting at minimum noise; and one for minimum fuel consumption. The parametric analysis approach enables the visualisation of the effect of cycle choices (overall pressure ratio, bypass ratio, combustor outlet temperature) on parameters such as engine size, weight, specific thrust, specific fuel consumption, noise and mission fuel. It is shown that noise reduction comes at the expense of fuel consumption, reducing the energy conversion efficiency of the system. Nevertheless the proposed tool allows the performance engineer to make appropriate choices for given design targets.

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“…1. Unlike 'component build-up' approach to weight estimation, the engine weight modelled by WeiDim is based on cycle parameters analysis, as originally developed by Gerend and Roudhill [22]. Dividing the engine overall weight into two parts (fan and gas generator) provides this method with both precision and robustness.…”

Section: Engine Weight and Dimensions Modellingmentioning

confidence: 99%

Performance Analysis and Optimization of a Gas Turbine Cycle Integrated with an Internal Combustion Wave Rotor

Lenoble

Ogaji

2010

Proceedings of the Institution of Mechanical Engineers, Part A:

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In an effort to answer the current needs for more performing and energy efficient gas turbine engines, unsteady pressure gain devices are currently under great focus. This article describes the performance analysis of a novel turbine engine utilizing an internal combustion wave rotor. The performance of this engine is compared to that of a conventional engine, first using its original bypass ratio—fan pressure ratio configuration, and then an optimized configuration. The novel cycle engine is found to be more efficient, reducing specific fuel consumption by approximately 37 per cent for the non-optimized condition, whereas the optimized engine has a potential for reducing by about 40 per cent the fuel needed for a typical long-range aircraft mission. This high potential reduction in fuel consumption encourages more detailed studies based on more sophisticated models, taking into account cycle losses, emissions, and transient behaviours.

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Correlation of gas turbine engine weights and dimensions

Cited by 9 publications

References 1 publication

Evaluation of aero gas turbine preliminary weight estimation methods

Evaluation of aero gas turbine preliminary weight estimation methods

Effect of jet noise reduction on gas turbine engine efficiency

Performance Analysis and Optimization of a Gas Turbine Cycle Integrated with an Internal Combustion Wave Rotor

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