Conceptual design and integration of a propulsion system for a supersonic transport aircraft

2021 ◽  
pp. 095441002110169
Author(s):  
Rhys Hutchinson ◽  
Jeremy Lawrence ◽  
Keith F Joiner
Keyword(s):  
High Speed ◽  
Engine Performance ◽  
Cost Effective ◽  
Flight Test ◽  
Combined Cycle ◽  
Propulsion System ◽  
Technological Advancement ◽  
High Speed Design ◽  
Passenger Aircraft ◽  
Multifactor Regression

Despite 50 years of technological advancement since the inception of Concorde, research on supersonic passenger aircraft has only recently resulted in design and flight test of several small 12 to 55-passenger business jets with supersonic cruises between Mach 1.2 and 2.2. Analytical research designs of larger 300-passenger aircraft have been conducted only to speeds of Mach 2.0 and 2.2, mainly avoiding moving beyond turbojet propulsion. This research extends on an earlier multifactor regression sizing study to determine in greater design detail whether the configuration of a 200-passenger Mach 3.0 aircraft is feasible using extant technology. This research article is the second part of two and covers a suitable and cost-effective propulsion system for the executive supersonic passenger aircraft. Through this high-speed design, the research examines modern propulsion technology and the performance advancements it affords through higher efficiencies, higher metallurgical thermal limits, variable cycle engines and variable stator technology. The analysis was conducted on several potential propulsion systems using GasTurb software to obtain engine performance data. The performance results led to a combined cycle turbofan–ramjet engine as being the engine that could yield the most extensive range for the aircraft. Further investigation is needed on aircraft noise, engine emissions, the accuracy of the thrust-critical lift-to-drag ratios and the aeroelastic effects that can be closely coupled to noise and performance.

Conceptual aerodynamic design of an executive supersonic passenger aircraft – ESPA

2021 ◽  
pp. 095441002110251
Author(s):  
Jeremy P Lawrence ◽  
Rhys J Hutchinson ◽  
Keith F Joiner
Keyword(s):  
Aircraft Design ◽  
Flight Test ◽  
Research Literature ◽  
Multidisciplinary Optimization ◽  
Technological Advancement ◽  
Design Evolution ◽  
Design Detail ◽  
Shock Wave Formation ◽  
Passenger Aircraft ◽  
Multifactor Regression

Despite 50 years of technological advancement since the inception of Concorde, research on supersonic passenger aircraft has only recently resulted in design and flight test of several small 12- to 55-passenger business jets with supersonic cruises between Mach 1.2 and 2.2. Analytical research designs of larger 300-passenger aircraft have been conducted only to speeds of Mach 2.0 and 2.2, mainly avoiding moving beyond turbojet propulsion. This research extends on an earlier multifactor regression sizing study to determine in greater design detail what the configuration of a 200-passenger Mach 3.0 aircraft could be using extant technology. This research article is the first part of two and covers the conceptual aircraft design evolution focussing on the aerodynamics, wing and fuselage. In contrast, the second article covers engine conceptual design and placement. Wing shape optimization is performed using fundamental CFD analysis to arrive at a configuration suitable for both subsonic and supersonic flight. Noise considerations and shock wave formation drive further design iterations based on the research literature. The viability of this research design informs a future multidisciplinary optimization like those recently published in the literature for smaller supersonic business jets.

A Study of Two Variable Cycle Engine Concepts for High Speed Civil Aircraft

2020 ◽  
Author(s):  
Jiyuan Zhang ◽  
Min Chen ◽  
Hailong Tang ◽  
Xin Liu
Keyword(s):  
High Speed ◽  
Engine Performance ◽  
Propulsion System ◽  
Parameter Determination ◽  
Control Law ◽  
Performance Requirement ◽  
Civil Aircraft ◽  
Matching Mechanism ◽  
Aircraft Propulsion System ◽  
Cycle Parameter

Abstract High speed civil aircraft has become a promising field with the development of globalization. The propulsion system is an indispensable part of the aircraft. Conventional engines have difficulty meeting the performance requirement of the high-speed civil aircraft. In this article, two variable cycle engines were studied to preliminarily as aircraft propulsion system. Their performance and matching mechanism were analyzed and compared with each other. Firstly, the cycle parameters design was conducted to explain the principle of cycle parameter determination for the high-speed civil aircraft. Secondly, the control law of variable geometry components was studied to optimize engine performance during supersonic cruising. Finally, the throttling process with constant airflow was studied to solve the problem of thrust surplus during subsonic cruising. According to this study, given same cycle parameters, the engine with variable fan stage can produce equal or slightly higher thrust with slightly less fuel consumption than the engine with core-driven-fan stage. The engine with core-driven-fan stage has advantages in aero-dynamical stabilities. It can also throttle to slightly lower thrust level during subsonic cruising. Considering the advantages in performance and derived development comprehensively, the engine with variable fan stage is a better option for high speed civil aircraft.

scholarly journals Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory

2019 ◽  
Vol 304 ◽  
pp. 03001 ◽  
Author(s):  
Ali Can Ispir ◽  
Pedro Miguel Gonçalves ◽  
Bayindir H. Saracoglu
Keyword(s):  
Computer Aided Design ◽  
High Speed ◽  
Differential Evolution Algorithm ◽  
Ground Level ◽  
Inviscid Flow ◽  
Combined Cycle ◽  
Propulsion System ◽  
Civil Aviation ◽  
Thermodynamic Simulations ◽  
Aided Design

Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of STRATOFLY aircraft consists of combination of two different type of engines: an array of air turbo rockets and a dualmode ramjet/scramjet. In the present study, 1D transient thermodynamic simulations for this combined cycle propulsion plant have been conducted between Mach 0 to 8 by utilizing 1D inviscid flow transport relations, numerical tools availablein EcosimPro software platform and the European Space Propulsion System Simulation libraries. The optimized engine parameters are achieved by coupling EcosimPro software with Computer Aided Design Optimization which is a differential evolution algorithm developed at the von Karman Institute.

scholarly journals Conceptual Design of Turbo-Accelerator for HST Combined Cycle Engine

1992 ◽  
Author(s):  
R. Yanagi ◽  
M. Morita ◽  
Y. Watanabe ◽  
H. Itahara ◽  
Y. Sasaki ◽  
...  
Keyword(s):  
Conceptual Design ◽  
High Speed ◽  
Low Noise ◽  
Combined Cycle ◽  
Propulsion System ◽  
Supersonic Transport ◽  
Low Pressure Turbine ◽  
Ramjet Engine ◽  
Speed Range ◽  
Jet Velocity

Hypersonic Transport Propulsion System Research (HYPR) Project was started in 1900 to develop technologies for the propulsion system of a Mach 5 Hypersonic Civil Transport, which could be environmentally acceptable and economically viable. The engine being studied is the methane fueled combined cycle engine composed of a turbo-accelerator for low speed range and a ramjet engine for high speed range. what is called a turbo/ramjet engine. The turbo-accelerator is required to meet the low noise regulations at take-off and achieve high specific thrust at high speed flight like the second generation SST (Supersonic Transport) engine. The single bypass turbofan engine (SBE) with variable cycle concept was selected as the turbo-accelerator engine to meet the above requirements in one engine. The engine was conceived to have variable geometry in compressor stator, low pressure turbine stator, fan bypass flow nozzle aren and exhaust nozzle area for low jet velocity at take-off and high jet velocity at altitude high speed and be equipped with a mixer ejector in the exhaust nozzle for further noise reduction. This paper describes the cycle study and conceptual design of the demonstrator of a turbo-accelerator engine being planned to be tested in 1903.

The Radio Probe™: A New Measurement Tool for High Speed Integrated Circuits

2005 ◽  
Author(s):  
Mark Kimball
Keyword(s):  
Integrated Circuits ◽  
Integrated Circuit ◽  
High Speed ◽  
Attenuation Factor ◽  
Cost Effective ◽  
Frequency Measurement ◽  
Single Frequency ◽  
Measurement Tool ◽  
Probe Design ◽  
Differential Measurement

Abstract This article presents a novel tool designed to allow circuit node measurements in a radio frequency (RF) integrated circuit. The discussion covers RF circuit problems; provides details on the Radio Probe design, which achieves an input impedance of 50Kohms and an overall attenuation factor of 0 dB; and describes signal to noise issues in the output signal, along with their improvement techniques. This cost-effective solution incorporates features that make it well suited to the task of differential measurement of circuit nodes within an RF IC. The Radio Probe concept offers a number of advantages compared to active probes. It is a single frequency measurement tool, so it complements, rather than replaces, active probes.

scholarly journals 2D-3D integration of hexagonal boron nitride and a high-κ dielectric for ultrafast graphene-based electro-absorption modulators

2021 ◽  
Vol 12 (1) ◽  
Author(s):  
Hitesh Agarwal ◽  
Bernat Terrés ◽  
Lorenzo Orsini ◽  
Alberto Montanaro ◽  
Vito Sorianello ◽  
...  
Keyword(s):  
Boron Nitride ◽  
Hafnium Oxide ◽  
High Speed ◽  
Hexagonal Boron Nitride ◽  
Temperature Stability ◽  
Cost Effective ◽  
Fold Increase ◽  
Building Blocks ◽  
High Quality ◽  
New Device

AbstractElectro-absorption (EA) waveguide-coupled modulators are essential building blocks for on-chip optical communications. Compared to state-of-the-art silicon (Si) devices, graphene-based EA modulators promise smaller footprints, larger temperature stability, cost-effective integration and high speeds. However, combining high speed and large modulation efficiencies in a single graphene-based device has remained elusive so far. In this work, we overcome this fundamental trade-off by demonstrating the 2D-3D dielectric integration in a high-quality encapsulated graphene device. We integrated hafnium oxide (HfO2) and two-dimensional hexagonal boron nitride (hBN) within the insulating section of a double-layer (DL) graphene EA modulator. This combination of materials allows for a high-quality modulator device with high performances: a ~39 GHz bandwidth (BW) with a three-fold increase in modulation efficiency compared to previously reported high-speed modulators. This 2D-3D dielectric integration paves the way to a plethora of electronic and opto-electronic devices with enhanced performance and stability, while expanding the freedom for new device designs.

scholarly journals Scale-Up Preparation of Crocins I and II from Gardeniajasminoides by a Two-Step Chromatographic Approach and Their Inhibitory Activity Against ATP Citrate Lyase

Molecules ◽  
2021 ◽  
Vol 26 (11) ◽  
pp. 3137
Author(s):  
Shuguang Guan ◽  
Qiaoli Pu ◽  
Yinan Liu ◽  
Honghong Wu ◽  
Wenbo Yu ◽  
...  
Keyword(s):  
Inhibitory Activity ◽  
High Speed ◽  
Scale Up ◽  
Cost Effective ◽  
Atp Citrate Lyase ◽  
Gardenia Jasminoides ◽  
Citrate Lyase ◽  
Human Disorders ◽  
Ic50 Values ◽  
Counter Current

Crocins are highly valuable natural compounds for treating human disorders, and they are also high-end spices and colorants in the food industry. Due to the limitation of obtaining this type of highly polar compound, the commercial prices of crocins I and II are expensive. In this study, macroporous resin column chromatography combined with high-speed counter-current chromatography (HSCCC) was used to purify crocins I and II from natural sources. With only two chromatographic steps, both compounds were simultaneously isolated from the dry fruit of Gardenia jasminoides, which is a cheap herbal medicine distributed in a number of countries. In an effort to shorten the isolation time and reduce solvent usage, forward and reverse rotations were successively utilized in the HSCCC isolation procedure. Crocins I and II were simultaneously obtained from a herbal resource with high recoveries of 0.5% and 0.1%, respectively, and high purities of 98.7% and 99.1%, respectively, by HPLC analysis. The optimized preparation method was proven to be highly efficient, convenient, and cost-effective. Crocins I and II exhibited inhibitory activity against ATP citrate lyase, and their IC50 values were determined to be 36.3 ± 6.24 and 29.7 ± 7.41 μM, respectively.

Narrowing longitudinally coupled prefabricated slab track maintenance duration with field data analysis of slab deformation under high temperature

2021 ◽  
pp. 095440972098626
Author(s):  
Zai-Wei Li ◽  
Xiao-Zhou Liu ◽  
Hong-Yao Lu ◽  
Yue-Lei He
Keyword(s):  
High Temperature ◽  
High Speed ◽  
Ride Comfort ◽  
Cost Effective ◽  
Periodic Variation ◽  
Longitudinal Force ◽  
Distribution Analysis ◽  
High Speed Rail ◽  
Track Maintenance ◽  
Slab Track

The deformation of longitudinally coupled prefabricated slab track (LCPST) due to high temperature may lead to a reduction in ride comfort and safety in high-speed rail (HSR) operation. It is thus critical to understand and track the development of such defects. This study develops an online monitoring system to analyze LCPST deformation at different slab depths under various temperatures. The trackside system, powered by solar energy with STM8L core that is ultra-low in energy consumption, is used to collect data of LCPST deformation and temperature level uninterruptedly. With canonical correlation analysis, it is found that LCPST deformation presents similar periodic variation to yearly temperature fluctuation and large longitudinal force may be generated as heat accumulates in summer, thereby causing track defects. Then the distribution of temperature and deformation data is categorized based on fuzzy c-means clustering. Through the distribution analysis, it is suggested that slab inspection can be shortened to 6 hours, i.e. from 10:00 am to 4:00 pm, reducing 14.3% track inspection workload from the current practice. The price of workload reduction is only a 2% chance of missed detection of slab deformation. The finding of this research can be used to enhance LCPST monitoring efficiency and reduce interruption to HSR operation, which is an essential step in promoting reliable and cost-effective track service.

Integrated Vehicle Comparison of Turbo-Ramjet Engine and Pulsed Detonation Engine

2002 ◽  
Vol 125 (1) ◽  
pp. 257-262 ◽  
Author(s):  
T. Kaemming
Keyword(s):  
Life Cycle Cost ◽  
High Speed ◽  
Fuel Efficiency ◽  
Pressure Rise ◽  
Propulsion System ◽  
Cross Sectional ◽  
Pulsed Detonation Engine ◽  
Pulsed Detonation ◽  
Large Matrix ◽  
Detonation Engine

The pulsed detonation engine (PDE) is a unique propulsion system that uses the pressure rise associated with detonations to efficiently provide thrust. A study was conducted under the direction of the NASA Langley Research Center to identify the flight applications that provide the greatest potential benefits when incorporating a PDE propulsion system. The study was conducted in three phases. The first two phases progressively screened a large matrix of possible applications down to three applications for a more in-depth, advanced design analysis. The three applications best suited to the PDE were (1) a supersonic tactical aircraft, (2) a supersonic strike missile, and (3) a hypersonic single-stage-to-orbit (SSTO) vehicle. The supersonic tactical aircraft is the focus of this paper. The supersonic, tactical aircraft is envisioned as a Mach 3.5 high-altitude reconnaissance aircraft with possible strike capability. The high speed was selected based on the perceived high-speed fuel efficiency benefits of the PDE. Relative to a turbo-ramjet powered vehicle, the study identified an 11% to 21% takeoff gross weight (TOGW) benefit to the PDE on the baseline 700 n.mi. radius mission depending on the assumptions used for PDE performance and mission requirements. The TOGW benefits predicted were a result of the PDE lower cruise specific fuel consumption (SFC) and lower vehicle supersonic drag. The lower vehicle drag resulted from better aft vehicle shaping, which was a result of better distribution of the PDE cross-sectional area. The reduction in TOGW and fuel usage produced an estimated 4% reduction in life cycle cost for the PDE vehicle. The study also showed that the simplicity of the PDE enables concurrent engineering development of the vehicle and engine.

On the exergetic effectiveness of combined-cycle engines for high speed propulsion

Energy ◽  
2013 ◽  
Vol 51 ◽  
pp. 382-394 ◽  
Author(s):  
Víctor Fernández-Villacé ◽  
Guillermo Paniagua
Keyword(s):  
High Speed ◽  
Combined Cycle
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