Journal of Propulsion and Power
About: Journal of Propulsion and Power is an academic journal. The journal publishes majorly in the area(s): Propellant & Combustion. It has an ISSN identifier of 0748-4658. Over the lifetime, 5256 publication(s) have been published receiving 122224 citation(s).
Topics: Propellant, Combustion, Combustor, Nozzle, Mach number
Papers published on a yearly basis
TL;DR: The chemical, physical, and mechanical characteristics of nickel-based superalloys are reviewed with emphasis on the use of this class of materials within turbine engines as mentioned in this paper, and the role of major and minor alloying additions in multicomponent commercial cast and wrought super-alloys is discussed.
Abstract: The chemical, physical, and mechanical characteristics of nickel-based superalloys are reviewed with emphasis on the use of this class of materials within turbine engines. The role of major and minor alloying additions in multicomponent commercial cast and wrought superalloys is discussed. Microstructural stability and phases observed during processing and in subsequent elevated-temperature service are summarized. Processing paths and recent advances in processing are addressed. Mechanical properties and deformation mechanisms are reviewed, including tensile properties, creep, fatigue, and cyclic crack growth. I. Introduction N ICKEL-BASED superalloys are an unusual class of metallic materials with an exceptional combination of hightemperature strength, toughness, and resistance to degradation in corrosive or oxidizing environments. These materials are widely used in aircraft and power-generation turbines, rocket engines, and other challenging environments, including nuclear power and chemical processing plants. Intensive alloy and process development activities during the past few decades have resulted in alloys that can tolerate average temperatures of 1050 ◦ C with occasional excursions (or local hot spots near airfoil tips) to temperatures as high as 1200 ◦ C, 1 which is approximately 90% of the melting point of the material. The underlying aspects of microstructure and composition that result in these exceptional properties are briefly reviewed here. Major classes of superalloys that are utilized in gas-turbine engines and the corresponding processes for their production are outlined along with characteristic mechanical and physical properties.
TL;DR: In this article, the authors describe ongoing research efforts in the scramjet community on cavity e ame holders, a concept for holding and stabilization in supersonic combustors, and discuss open questions impacting the effectiveness of the cavities as a holding device.
Abstract: This paper describes ongoing research efforts in the scramjet community on cavity e ame holders, a concept for e ame holding and stabilization in supersonic combustors. During the last few years, cavities have gained the attention of the scramjet community as a promising e ame-holding device, owing to results obtained in e ight tests and to feasibility demonstrations in laboratory-scale supersonic combustors. However, comprehensive studies are needed to determine the optimal cone guration that will yield the most effective e ame-holding capability with minimum losses. The e owe eld characteristics of cavities and research efforts related to cavities employed in lowand high-speed e ows are summarized. Open questions impacting the effectiveness of the cavities as e ame holders in supersonic combustors are discussed.
TL;DR: In this paper, a review of the evolution and maturity of SU-scramjet engines over the last 40 years is presented in terms of efforts completed or proceeding in the United States, Russia, France, Germany, Japan, Australia, and other countries.
Abstract: Ageneralreviewoftheemergenceandmaturingofsupersoniccombustionramjet (scramjet)enginetechnologies overthelast 40 years is presented. The review isgiven in terms of theeffortscompleted or proceeding in theUnited States, Russia, France, Germany, Japan, Australia, and other countries. A brief account of the challenges of scramjet combustor development is given, and attention is directed toward other source references for more detailed accounts of technology evolution. Two emerging scramjet applications are identie ed, namely, hydrogenfueledhigh-speed engines foraccess to spaceand hydrocarbon-fueled enginesforhypersonicair-launched missiles.
TL;DR: A review of the literature on the effects of freestream turbulence, surface curvature, and hole shape on the performance of film cooling is presented in this article. But, it is difficult to predict film cooling performance because of the inherent complex flowfields along the airfoil component surfaces in turbine engines.
Abstract: The durability of gas turbine engines is strongly dependent on the component temperatures. For the combustor and turbine airfoils and endwalls, film cooling is used extensively to reduce component temperatures. Film cooling is a cooling method used in virtually all of today's aircraft turbine engines and in many power-generation turbine engines and yet has very difficult phenomena to predict. The interaction of jets-in-crossflow, which is representative of film cooling, results in a shear layer that leads to mixing and a decay in the cooling performance along a surface. This interaction is highly dependent on the jet-to-crossflow mass and momentum flux ratios. Film-cooling performance is difficult to predict because of the inherent complex flowfields along the airfoil component surfaces in turbine engines. Film cooling is applied to nearly all of the external surfaces associated with the airfoils that are exposed to the hot combustion gasses such as the leading edges, main bodies, blade tips, and endwalls. In a review of the literature, it was found that there are strong effects of freestream turbulence, surface curvature, and hole shape on the performance of film cooling. Film cooling is reviewed through a discussion of the analyses methodologies, a physical description, and the various influences on film-cooling performance.
TL;DR: In this paper, the results of controlled continuous spin detonation of various fuels in liquid-propellant rocket motors and ramjet combustors are reported, and the flow structure, existence conditions, and basic properties of continuous detonation are considered.
Abstract: Results on controlled continuous spin detonation of various fuels in liquid-propellant rocket motors and ramjet combustors are reported. Schemes of chambers, combustion in transverse detonation waves, and typical photographic records of transverse detonation waves are given. The flow structure, existence conditions, and basic properties of continuous detonation are considered. An analysis of physical, chemical, and geometric parameters determining spin detonation is presented. Results of studying continuous spin detonation of C 2 H 2 + air and H 2 + air mixtures in an annular ducted chamber 30.6 cm in diameter are reported. The range of existence of continuous spin detonation in fuel-air mixtures is determined as a function of the governing parameters. In the case of high-quality mixing, the transverse detonation wave velocity and structure are extremely stable in a wide range of the ratios of propellant components and in the examined range of pressures in the chamber.
Related Journals (5)
23.6K papers, 656.8K citations
Combustion and Flame
10.6K papers, 435.4K citations
Journal of Aircraft
9.9K papers, 182.9K citations
Experiments in Fluids
5.8K papers, 184.5K citations
Physics of Fluids
29.4K papers, 941K citations