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Under the dual effects of aerodynamic heating and high-power electronic equipment heating, the heat sink and power demand of advanced high-speed aircraft have been exponentially rising, which seriously restricts the aircraft performance. To improve system cooling and power supply performance and reduce engine performance loss, a power and thermal m...
Citations
... In addition to thermodynamic characteristic optimisation, IPTMS optimisation can also achieve light weight at the system level. Rong et al. [95] proposed a system-level analysis method to minimise the total fuel weight penalty for a simplified IPTMS with energy recovery. They adopted the equivalent mass method for analysis and compared the performance of three cooling strategies of the IPTMS. ...
Projects related to green aviation designed to achieve fuel savings and emission reductions are increasingly being established in response to growing concerns over climate change. Within the aviation industry, there is a growing trend towards the electrification of aircraft, with more-electric aircraft (MEA) and all-electric aircraft (AEA) being proposed. However, increasing electrification causes challenges with conventional thermal management system (TMS) and power management system (PMS) designs in aircraft. As a result, the integrated power and thermal management system (IPTMS) has been developed for energy-optimised aircraft projects. This review paper aims to review recent IPTMS progress and explore potential design solutions for civil aircraft. Firstly, the paper reviews the IPTMS in electrified propulsion aircraft (EPA), presenting the architectures and challenges of the propulsion systems, the TMS cooling strategies, and the power management optimisation. Then, several research topics in IPTMS are reviewed in detail: architecture design, power management optimisation, modelling, and analysis method development. Through the review of state-of-the-art IPTMS research, the challenges and future opportunities and requirements of IPTMS design are discussed. Based on the discussions, two potential solutions for IPTMS to address the challenges of civil EPA are proposed, including the combination of architecture design and power management optimisation and the combination of modelling and analysis methods.
... Under the double heating effects of high-power electronic apparatus and aerodynamic, the power demand and heat sink of superior high-speed aircraft have been rising exponentially, which seriously restricts the aircraft performance. A thermal/power management system (TPMS) was used to improve system cooling [15]. However, the optimization variables were not consisting of the fan duct heat exchanger structure size, cooling air flow rate, and compressor outlet temperature. ...
Recently, engine design and control systems have been developed using data-driven modeling techniques to specify the in-cylinder complicated combustion process. The cooling fan performance is highly influenced by several factors that are determined based on what is called (DOE) «design of experiments». These factors include blade tip clearance, pitch angle, and distance from a radiator. This work presents a method to improve the cooling fan performance of an engine by designing a Six Sigma technique using Control, Improve, Analyze, Measure, and Define (CIAMD). First, let's assess the existing cooling fan performance and define its problem. Then, let's specify the parameters that affect fan performance to be optimized. Next, let's conduct a sensitivity analysis and evaluate the manufacturing control of the developed cool Fan. The primary fan does not distribute air enough by the radiator to keep the machine cool throughout hard circumstances. First, the work demonstrates how to develop an experiment to examine the influence of three performance elements: blade pitch angle, blade-tip clearance, and fan distance from the radiator. In order to improve the performance of the cooling fan, the Box-Behnken design is adopted for testing quadratic (non-linear) effects. It then indicates how to predict optimal quantities for every element, to produce a technique that makes airflows above the objective of 1486.6 m 3 /h when utilizing experimental measurements. Finally, it reveals how to operate simulations to confirm that this method creates airflow based on the specifications with more additional fans manufactured performance of 99.999 %. The results of S and X-bar control charts indicate that the manufacturing process is statistically under control
... When an aircraft is equipped with an ACS, extra energy is consumed to transport a system of a certain weight, overcome aerodynamic drag, etc. All the extra energy consumed can be generalized to the fuel consumption of the aircraft [36][37][38]. The aerodynamic drag caused by air inhalation and shaft power extraction are considered in this calculation, and the fuel weight penalty method [39] can be used to determine the weight of each route. ...
Air cycle systems (ACSs) are primarily used in aircraft environmental control systems (ECSs) to provide a suitable cabin temperature and pressure environment for passengers and avionics. It comprises heat exchangers, compressors, turbines, water separators, and various other components that are interconnected to form an information-transmission network. Traditional research on ACSs has focused primarily on their thermal performance. This study abstracted ACSs into network graphs based on their information-transmission characteristics, determined the weight of each information-transmission route using the fuel weight penalty method, calculated and compared the order degree of different ACSs using the structure entropy method, and measured the importance of each component using centrality for the first time. The results showed that the order degree of the ACSs gradually increased with an increase in the number of wheels in the air cycle machine (ACM), and ACSs with high-pressure water separation had a higher order degree under wet conditions than under dry conditions. Moreover, based on the centrality of each vertex in the graphs, the ACM and secondary heat exchanger in the ACS were fundamentally important and should be focused on during the system design. The methodology proposed in this study provides a theoretical basis for the evaluation of the ACS organizational structure and the design performance of components.
... Emerging technology, including small satellites for space craft propulsion and wireless and independent instruments for vehicles and airplanes, demand lightweight, and compact cooler systems for optimal operation [1,2]. Owing to their attributes, such as modular systems with high reliability and without moving mechanic parts or cryogenic fluids, all solid-state crycoolers have attracted increasing attention as possible candidates for satisfying the aforementioned requirements [3][4][5][6][7]. ...
... The optimal θ SPR was measured for the interface prism-ITO-CdSe/ ZnS(QDs) under illumination at three excitation wavelengths (405, 532, and 640 nm). Table 1 shows the measured optimal θ SPR and a comparison with the theoretical calculations that were obtained by using Equation (1). The complex refractive index for ITO (ñ 1 ) and the prism (ñ 2 ) used for the calculations are presented in Table 2, and ñ 3 = 1 because medium 3 is air [27]. ...
... The demand for high-power electronic chips, supercomputing, hybrid vehicles and other technological products with increasing performance requirements has set thermal management of electronics as a centerpiece of the technology development (Lijun et al., 2020;Li et al., 2020;Shurong et al., 2020;Rong et al., 2021). In recent years, substantial efforts have been made towards developing novel cooling solutions for high heat fluxes since traditional single phase cooling technologies are no longer able to meet the stable and reliable cooling requirements. ...
In previous studies, we introduced the concept of a compact heat sink that combines an evaporator and an expansion device into a single unit for high heat flux applications. As the high-pressure subcooled liquid refrigerant expands in an array of oblique orifices, a spray cone is formed which directly impinges on the heated surface, removing large quantities of heat by boiling and evaporation of the liquid film. Numerous applications of the concept can be sought when one considers its integration with compact compressors (i.e., cooling of power electronics, batteries etc.), since it combines the low thermal resistance of impinging jets with below-ambient evaporating temperatures. In this paper, we evaluate the use of laser-ablated square micro pillars on the heated surface as a means to enhance the heat removal capability of the system. Microscopic and interferometry images of the resulting surfaces are presented and evaluated regarding its final topography and extended heat transfer surface area. Experiments conducted with R-134a using a two-orifice expansion device and enhanced surfaces resulted in a cooling capacity of 230 W (35.9 W/cm 2) with a heated surface temperature always below 22.9 • C and average heat transfer coefficients as high as 46,369 W/(m 2 K). In comparison with mirror polished surfaces, this represents a thermal conductance increase of 91%, resulting in a significant reduction of the heated surface temperature.
... Then, the total power generation of the fuel vapor turbine, W f , can be calculated. (5) Fuel weight penalty calculation In this paper, the total mass of the take-off period method is employed [16][17][18]. The mass and power consumption of the PTMS can be converted into fuel consumption to evaluate their impact on the performance of the vehicle. ...
... The mass and power consumption of the PTMS can be converted into fuel consumption to evaluate their impact on the performance of the vehicle. Ignoring the weight of the fixed pipeline and power consumption of the fuel pump, the total fuel weight penalty of the PTMS is calculated with Equations (31) and (32) [16]: ...
The scramjet of hypersonic vehicles faces severe high-temperature challenges, but the heat sink available for scramjet cooling is extremely finite. It is necessary to optimize its power and thermal management system (PTMS) with a finite heat sink of hydrocarbon fuel. This paper proposes a two-level optimization method for the PTMS of hypersonic vehicles at Mach 6. The PTMS is based on a supercritical carbon dioxide (SCO2) closed Brayton cycle, and its heat sink is airborne hydrocarbon fuel. System-level optimization aims to obtain the optimal system parameters for the PTMS. The minimum fuel weight penalty and the minimum heat sink consumption of fuel are the optimization objectives. The segmental (SEG) method is used to analyze the internal temperature distribution of fuel–SCO2 heat exchangers in the system-level optimal solution set. This ensures the selected optimal solutions meet the requirement of a pinch temperature difference greater than or equal to 10 °C. Further, the component-level optimization for the fuel–SCO2 heat exchanger is carried out based on the selected optimal solutions. The lightest weight of the heat exchanger and the minimum entropy production are the optimization objectives in this step. Finally, the optimal system parameters and the optimal key component parameters can be searched using this presented two-level optimization method.
... Aircraft environmental control system (abbreviated as "aircraft environmental control system") is a vital part of the aircraft to ensure the life safety and normal operation of airborne personnel and electronic equipment [1][2][3][4]. e bleed system of the aircraft air circulation control system mainly takes the engine compressor as the pressurization source [5][6][7][8]. Due to the direct influence of engine operating conditions, the temperature and pressure of engine compressor bleed air fluctuate greatly and cannot directly enter the refrigeration system. ...
This paper studies the aircraft air circulation system and proposes a new architecture of the aircraft air circulation system. Combined with the neural network algorithm, the numerical simulation results of turbine, compressor, and heat exchanger are fitted and predicted, and the accuracy of the simulation model is verified by comparing with the experimental results. Comparing and analyzing the booster, F-15, F-35, and the newly proposed air circulation system, the engine bleed air volume consumed by the system under different flight conditions is obtained. The results show that the newly proposed air circulation system can save up to 71.4% of the engine bleed air compared with the simple boost and 29.8% of the engine bleed air compared with the F-35. The new air circulation system proposed in this paper can effectively improve the energy utilization rate of the system and reduce the consumption of engine bleed air.
... Sustainable energy systems are required to provide energy demand due to the rapid urbanizations and decline of traditional energy resources (Babatunde et al., 2020;Bezai et al., 2021;Kalua, 2020;Mikkola and Lund, 2014). Global warming concerns toward a new sustainable energy generation system provides a way for optimization and design of integrated energy system (Rong et al., 2021;Bertsch et al., 2007;Wu et al., 2021). The key reason behind the deployment of grid-connected integrated sustainable energy systems (ISES) aims to ensure better energy supply with an emission reduction for enhanced energy security and reliable sustainable energy system (Aziz et al., 2019;Halabi et al., 2017;Sunitiyoso et al., 2020;Tol et al., 2021). ...
Purpose
Earlier most of the research groups have designed and developed hybrid renewable energy system models with technological, scientific and industrial advancement for the energy systems, but slight attention has been paid towards the grid-connected sustainable urban residential energy systems (SUR e S) for metropolitan cities. The current research wishes to design, model and analyze grid-connected energy system for residential applications for sustainable urban residential energy system. The works aims to explore the potential of the augmented energy system for grid-connected energy system.
Design/methodology/approach
The proposed grid-connected SUR e S are validated for a sample location at New Delhi (India) with a hybrid optimization model for electric renewable (HOMER) software to define and understand the various load profile. It presents the sensitivity analysis approach to validate the design of the proposed energy system.
Findings
The obtained results reports the key barriers, proposed model and scenarios for sustainable urban energy system development.
Research limitations/implications
Similar approaches can be replicated to design and develop an independent, self-sustainable cleaner and environmental-friendly energy system in the future scenario for the extension of complex grid infrastructures.
Practical implications
It will assist the stakeholder in solving the complex urban sustainability issues raised due to the shortage of energy.
Social implications
It will offer a clean and environment friendly sustainable energy resources with reduced carbon emissions. It will benefit sustainable energy resources with a mix of challenges and opportunities, to suggest an approach for implementation of efficient energy policies to optimize the existing and forthcoming energy systems.
Originality/value
The current research offers a design and model to analyze grid-connected energy system sustainable urban residential applications. It explores the potential of the augmented energy system. The proposed model are validated for a sample location with HOMER simulation software to define and understand various scenarios of the multiple load profile. The work presents the sensitivity analysis approach to validate the proposed energy system.
To extend the thermal endurance of the aircraft, a new fuel thermal management system with multi-return flow paths to the fuel tanks (MRFTS) is proposed. Compared with the traditional single return fuel tank system (SRFTS), the biggest difference is the hot fuel can also be returned to the auxiliary tanks in the MRFTS. The flow selector of the MRFTS is equipped with a temperature control strategy, which can keep the system temperature below but approaching the limit values to achieve the acceleration of the waste heat dissipation. And the fuel consuming sequence of the actual fuel tanks has been fully considered in this control strategy. By the numerical calculation of the high-power condition, the thermal endurance of the MRFTS is increased to 3319.8 s while the thermal endurance of the SRFTS is only 389.5 s, which means utilizing the large amount of the heat sink of the auxiliary tanks can significantly improve the aircraft thermal endurance. Furthermore, a mission profile with a long-time aircraft engagement is analyzed as well, which indicates that the MRFTS can control the system temperature not exceeding the limit values by the dynamic selections of the return tanks while the SRFTS cannot meet the thermal management requirements during the engagement stage. Therefore, the MRFTS can extend the aircraft thermal endurance effectively during the entire flight process with the high thermal load.
