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.

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.

Effect of Hot Probe Temperature on Ignition of Alcohol-to-Jet (ATJ) Fuel Spray under Aircraft Propulsion System Conditions

2021 ◽  
Author(s):  
Je Ir Ryu ◽  
Austen Motily ◽  
Tonghun Lee ◽  
Riccardo Scarcelli ◽  
Sibendu Som ◽  
...  
Keyword(s):  
Propulsion System ◽  
Fuel Spray ◽  
Hot Probe ◽  
Aircraft Propulsion System ◽  
Aircraft Propulsion

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.

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2005 ◽  
Vol 127 (1) ◽  
pp. 8-17 ◽  
Author(s):  
Milt Davis ◽  
Peter Montgomery
Keyword(s):  
System Performance ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Flight Simulation ◽  
Propulsion System ◽  
Test Facility ◽  
Flight Testing ◽  
Test Environment ◽  
Ground Test ◽  
Aircraft System

Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.

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

2021 ◽  
Author(s):  
Jiyuan Zhang ◽  
Min Chen ◽  
Hailong Tang ◽  
Xin Liu
Keyword(s):  
High Speed ◽  
Civil Aircraft

Aircraft Propulsion System Accident Causal Analysis

2000 ◽  
Author(s):  
Todd D. Jack ◽  
Carl N. Ford ◽  
Shari-Beth Nadell ◽  
Vicki Crisp
Keyword(s):  
Time Frame ◽  
Causal Analysis ◽  
Propulsion System ◽  
Mitigation Strategies ◽  
Transportation Safety ◽  
Future Research ◽  
Data Set ◽  
Depth Analysis ◽  
Aircraft Propulsion System ◽  
Engine Type

A causal analysis of aviation accidents by engine type is presented. The analysis employs a top-down methodology that performs a detailed analysis of the causes and factors cited in accident reports to develop a “fingerprint” profile for each engine type. This is followed by an in-depth analysis of each fingerprint that produces a sequential breakdown. Analysis results of National Transportation Safety Board (NTSB) accidents, both fatal and non-fatal, that occurred during the time period of 1990–1998 are presented. Each data set is comprised of all accidents that involved aircraft with the following engine types: turbofan, turbojet, turboprop, and turboshaft (includes turbine helicopters). During this time frame there were 1461 accidents involving turbine powered aircraft; 306 of these involved propulsion malfunctions and/ or failures. Analyses are performed to investigate the sequential relationships between propulsion system malfunctions or failures with other causes and factors for each engine type. Other malfunctions or events prominent within each data set are also analyzed. Significant trends are identified. The results from this study can be used to identify areas for future research into intervention, prevention, and mitigation strategies.

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