F100/F401 Augmented Turbofan Engines - High Thrust-to-Weight Propulsion Systems

1972 ◽  
Author(s):  
John F. Mcdermott
Keyword(s):  
Propulsion Systems ◽  
Turbofan Engines ◽  
High Thrust

Turbine Engine Icing Spray Bar Design Issues

1995 ◽  
Vol 117 (3) ◽  
pp. 406-412 ◽  
Author(s):  
C. S. Bartlett
Keyword(s):  
Supercooled Liquid ◽  
Propulsion System ◽  
Test Facility ◽  
Turbine Engine ◽  
Turbofan Engines ◽  
Free Jet ◽  
Spray System ◽  
Key Issues ◽  
Development Center ◽  
High Thrust

Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEDC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide the capability to conduct icing testing in either the direct-connect (connected pipe) or the free-jet mode. The requirements of a spray system for turbine engine icing testing are described, as are the techniques used at the AEDC ETF to simulate flight in icing conditions. Some of the key issues facing the designer of a spray system for use in an altitude facility are identified and discussed, and validation testing of the design of a new spray system for the AEDC ETF is detailed. This spray system enables testing of the newest generation of high-thrust turbofan engines in simulated icing conditions.

Transient Hydroelastic Analysis of Pump Performance of an SES-Waterjet System

2012 ◽  
Author(s):  
Michael R. Motley ◽  
Yin L. Young ◽  
Brant R. Savander
Keyword(s):  
Surface Effect ◽  
Dynamic Performance ◽  
Operating Conditions ◽  
Geometric Constraints ◽  
Propulsion Systems ◽  
Structural Dynamic ◽  
Surface Vessels ◽  
Hydroelastic Analysis ◽  
Cargo Capacity ◽  
High Thrust

Surface Effect Ships (SES) have great potential to increase the speed and cargo capacity of modern surface vessels. Waterjets are typically used for propulsion of SES because of the geometric constraints and its ability to absorb high thrust and power requirements. The objective of this paper is to investigate the transient hydroelastic performance of waterjet propulsion systems. The goal is to advance the fundamental understanding of the transient hydrodynamic and structural dynamic performance of waterjet propulsion systems with consideration for non-uniform inflow and transient fluid cavitation at heavily loaded operating conditions. Special attention is given to investigating the effects of flow non-uniformity and fluid cavitation on the system performance, as well as the structural dynamic performance of the rotor and stator blades.

scholarly journals Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): For CubeSats in LEO and to the Moon

Aerospace ◽  
2021 ◽  
Vol 8 (6) ◽  
pp. 169
Author(s):  
Ahmed E. S. Nosseir ◽  
Angelo Cervone ◽  
Angelo Pasini
Keyword(s):  
High Performance ◽  
System Analysis ◽  
Propulsion System ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Analysis And Design ◽  
Performance Space ◽  
Green Propellants ◽  
Commercial Off The Shelf ◽  
High Thrust

Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to overcome the growing challenges, particularly related to overcrowded LEOs, and to modern space application orbital maneuver requirements. Green monopropellants are gaining momentum in the design and development of small and modular liquid propulsion systems, especially for CubeSats, due to their favorable thermophysical properties and relatively high performance when compared to gaseous propellants, and perhaps simpler management when compared to bipropellants. Accordingly, a novel high-thrust modular impulsive green monopropellant propulsion system with a micro electric pump feed cycle is proposed. MIMPS-G500mN is designed to be capable of delivering 0.5 N thrust and offers theoretical total impulse Itot from 850 to 1350 N s per 1U and >3000 N s per 2U depending on the burnt monopropellant, which makes it a candidate for various LEO satellites as well as future Moon missions. Green monopropellant ASCENT (formerly AF-M315E), as well as HAN and ADN-based alternatives (i.e., HNP225 and LMP-103S) were proposed in the preliminary design and system analysis. The article will present state-of-the-art green monopropellants in the (EIL) Energetic Ionic Liquid class and a trade-off study for proposed propellants. System analysis and design of MIMPS-G500mN will be discussed in detail, and the article will conclude with a market survey on small satellites green monopropellant propulsion systems and commercial off-the-shelf thrusters.

Applications of combined electric, high-thrust propulsion systems.

1968 ◽  
Vol 5 (7) ◽  
pp. 785-791 ◽  
Author(s):  
ALFRED C. MASCY ◽  
DUANE W. DUGAN ◽  
SAMUEL W. PITTS
Keyword(s):  
Propulsion Systems ◽  
High Thrust

Turbine Engine Icing Spray Bar Design Issues

1994 ◽  
Author(s):  
C. Scott Bartlett
Keyword(s):  
Supercooled Liquid ◽  
Propulsion System ◽  
Test Facility ◽  
Turbine Engine ◽  
Turbofan Engines ◽  
Free Jet ◽  
Spray System ◽  
Key Issues ◽  
Development Center ◽  
High Thrust

Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEOC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide the capability to conduct icing testing in either the direct-connect (connected pipe) or the free-jet mode. The requirements of a spray system for turbine engine icing testing are described, as are the techniques used at the AEDC ETF to simulate flight in icing conditions. Some of the key issues facing the designer of a spray system for use in an altitude facility are identified and discussed, and validation testing of the design of a new spray system for the AEDC ETF is detailed. This spray system enables testing of the newest generation of high-thrust turbofan engines in simulated icing conditions.

Trajectory options for a manned mission to Mars using high-thrust propulsion systems

2021 ◽  
pp. 96-110
Author(s):  
Nikolay I. ARKHANGELSKIY ◽  
Evgeny I. MUZYCHENKO ◽  
Aleksey A. SINITSYN
Keyword(s):  
Rocket Engine ◽  
Earth Atmosphere ◽  
Optimal Solutions ◽  
Liquid Propellant ◽  
Propulsion Systems ◽  
Performance Factors ◽  
The Earth ◽  
Mission Duration ◽  
High Thrust ◽  
Nuclear Rocket

An analysis has been done of performance factors (mission duration, initial mass of the interplanetary crew transfer vehicle, velocity of the re-entry into the Earth atmosphere of the descent vehicle with the crew) for a single-spacecraft manned mission to Mars using high-thrust propulsion systems. Locally optimal solutions (in terms of delta-V budgets for the transfer) were found for the Earth–Mars–Earth transfer, with varying periods of waiting in Mars orbit, minimal distance to the Sun, as well as flight paths (direct Earth–Mars–Earth transfers vs. gravity assist maneuvers at Venus during Earth–Mars or Mars–Earth transfers). The proposed classification for locally optimal solutions is applicable to both high-thrust propulsion systems and low-thrust propulsion systems. A comparison of performance factors has been done for manned Martian mission options based on liquid-propellant engines and nuclear rocket engines with a 12,5 km/s constraint on the velocity of the manned re-entry vehicle in the Earth atmosphere. Key words: Manned mission to Mars, interplanetary transfer trajectory, high-thrust, liquid-propellant rocket engine, nuclear rocket engine, mission duration, initial mass of the interplanetary vehicle, re-entry velocity of a manned vehicle for returning the crew to Earth.

Generalized Thermodynamic Assessment of Concepts for Increasing the Efficiency of Civil Aircraft Propulsion Systems

2015 ◽  
Author(s):  
Florian Schmidt ◽  
Stephan Staudacher
Keyword(s):  
Thermodynamic Assessment ◽  
High Efficiency ◽  
Maximum Temperature ◽  
Propulsion Systems ◽  
Turbine Blade Cooling ◽  
Turbofan Engines ◽  
Blade Cooling ◽  
Ducted Fan ◽  
Efficiency Increase ◽  
High Level

It is known from thermodynamics that intercooling, recuperation, sequential combustion and constant-volume combustion increase the efficiency of thermal engines. Although these concepts are already analyzed at a high level of detail, no comparative and structured assessment of the theoretic and realistic efficiency increase for long-range turbofan engines is given. In light of this a generalized thermodynamic assessment of the mentioned technologies is conducted. First, current technological limits are ignored and the propulsive power is completely utilized. Theoretic efficiency improvements of over 24% are obtained. Second, the modelling is refined to include a ducted fan, turbine blade cooling and account for minimum blade height and maximum temperature at HPC outlet. Realistic efficiency improvements of still over 10% are identified. It is shown that significant increases in efficiency necessitate new engine architectures, outlining the restrictions of the current engine architecture. Intercooling is identified as the driving technology for high efficiency.

scholarly journals V/STOL Aircraft Gas Turbine Requirements

1967 ◽  
Author(s):  
O. G. Robbins
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Propulsion System ◽  
Propulsion Systems ◽  
Turbofan Engines ◽  
Gas Generators

The gas turbine requirements for V/STOL aircraft are strongly influenced by the type of airplane and the mission to be performed. For pusposes of this paper, the gas turbine requirements are established in several propulsion-system concepts which encompass the majority of engine requirements necessary to the V/STOL airplanes. General requirements are explored which are common to gas turbines regardless of mission or airplane type. Specific requirements for the air-superiority fighter airplane, the subsonic fighter attack airplane, and the transport-cargo type of airplane are discussed. These three types of airplanes are propelled by propulsion systems incorporating lift turbojet engines, turbofan engines, fans with remote gas generators, and turboprop engines.

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