Performance and Weight Estimates for an Advanced Open Rotor Engine

Hendricks, Eric S.; Tong, Michael T.

doi:10.2514/6.2012-3911

Cited by 28 publications

(19 citation statements)

References 4 publications

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“…For the estimation of counter-rotating propeller masses, a correlation given in Reference 32 was chosen and calibrated for advanced structural technology status. Obtained results showed good agreement with recent open rotor weight studies published by NASA 33 . The estimation of nacelle component and equipments masses refers to the methods described in Reference 24.…”

Section: Propulsion System Sizing and Performance Studiessupporting

confidence: 91%

Pre-Concept Performance Investigation of Electrically Powered Aero-Propulsion Systems

Seitz

Isikveren

Hornung

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Motivated by the possible prospect of zero in-flight emissions and the observed progress and perspectives in key electrical technologies, the pre-concept performance assessment of electrically powered aircraft propulsion systems is presented. The efficiency potentials of Electric Fan (EF) and Electric Open Rotor (EOR) power plant architectures are assessed and compared to advanced turbofan technology. In multi-disciplinary sizing and performance studies at the isolated propulsion system level, and, at the integrated vehicular level, optimum power plant design constellations are determined. Requirements for battery systems are derived, that would enable universally-electric, mid-size, short range air transport. Nomenclature Symbols:energy specific air range FN = net thrust g = gravity constant h = altitude L/D = aerodynamic efficiency m = mass n = rotational speed P = power PD = gravimetric power density TSPC = thrust specific power consumption V = velocity η = efficiency ϑ = cryogenic heat loss share Subscripts: 0 = true air speed 2 = thermodynamic station at fan front face 4 = thermodynamic station at burner exit A/C = aircraft bare = bare electric motor without cooling Batt = battery Carnot = Carnot factor cool = cooling des = design ec = energy conversion Fan = fan HPT = high pressure turbine HTS = high temperature superconducting IPC = intermediate pressure compressor in = inner jet/prop = jet / propeller load = thermal load LPT = low pressure turbine mech = mechanical min = minimum Mot = electric motor ov = overall P = Power pd = propulsive device PMAD = power management and distribution PPS = power plant system pr = propulsive Prop = propeller Propulsor = propulsor (fan / propeller) req = required sink = heat sink St = stage, stages supply = supply th = thermal T/O = take-off thrust = net thrust TOC = top of climb tr = transmission UESA = universally-electric systems architecture useful = useful

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Section: Propulsion System Sizing and Performance Studiessupporting

confidence: 91%

Pre-Concept Performance Investigation of Electrically Powered Aero-Propulsion Systems

Seitz

Isikveren

Hornung

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…A comparison of turbofan and open rotor (propfan) engines has been given by Hendricks and Tong [3]. The comparison to similar thrust sized engines is summarized in Table 1, taken from [3].…”

Section: Open Rotor Engines -Still An Open Question?mentioning

confidence: 99%

Open Rotor Engines—Still an Open Question?

Langston¹

2018

Mechanical Engineering

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A major factor in the continued domination of turbofan engines for economic airline propulsion, is the ability to increase bypass ratios. However, increasing fan diameters to go to ever higher bypass ratios increases nacelle weight, aerodynamic drag and duct losses. By eliminating the need for a fan duct, open rotor engines can effectively in-crease bypass ratios, resulting in a significant savings in fuel consumption. Open rotor engines have been under intermittent development since the 1980s, sub-ject to rising and falling of fuel prices. Technical challenges that continue in their de-ployment include noise reduction, airframe integration and protection from propel-ler/fan blade failure.

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“…The developed scaling technique is tested by scaling a baseline propeller map in order to obtain a map of a different propeller design. In a period when there is a renewed interest in turboprop aircraft [11,12] and open-rotor engines are always under investigation [4,[13][14][15][16][17][18], the scaling method proposed in this paper can be a valuable tool both for industrial and academic preliminary design studies.…”

Section: Afmentioning

confidence: 99%

“…After the calculation of the viscous losses and of the total propeller efficiency, one can use Eqs. (15)(16)(17)(18)(19)(20)(21) in order to calculate the ideal power coefficient, and subsequently use Eqs. (5)(6)(7)(8)(9)(10)(11)(12)(13)(14) once more to calculate the final ideal efficiency.…”

Section: Ideal Efficiency Estimationmentioning

confidence: 99%

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Novel Propeller Map Scaling Method

Giannakakis

Goulos

Laskaridis

et al. 2016

Journal of Propulsion and Power

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This paper presents a novel method of scaling a baseline propeller map η prop fJ;C P ;M in order to obtain the performance of a propeller with different design characteristics. The developed method employs a Goldstein/ Theodorsen model to calculate the ideal efficiency and a simple approach to estimate the propeller activity factor. The proposed scaling technique enables the use of a single propeller map for propellers with different design flight conditions, diameters, number of blades, activity factors, tip speeds, or power, provided that the blade sweep and airfoil distributions remain constant.

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Performance and Weight Estimates for an Advanced Open Rotor Engine

Cited by 28 publications

References 4 publications

Pre-Concept Performance Investigation of Electrically Powered Aero-Propulsion Systems

Pre-Concept Performance Investigation of Electrically Powered Aero-Propulsion Systems

Open Rotor Engines—Still an Open Question?

Novel Propeller Map Scaling Method

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