Design Aspects of Power Plants for V/STOL Aircraft

1967 ◽  
Author(s):  
J. F. Coplin
Keyword(s):  
Power Plants ◽  
Weight Ratio ◽  
Gas Generator ◽  
Extensive Experience ◽  
Thrust Vectoring ◽  
Two Generations ◽  
High Integrity ◽  
Integrated Concept ◽  
High Thrust ◽  
Efflux Velocity

Thrust in execess of that required for cruise and flight maneuvering is necessary to provide an aircraft with a VTOL capability. The extra thrust may be obtained by enlarged cruise engines with thrust vectoring or by retaining the optimum-size cruise engine possibly with thrust vectoring and adding a lift power plant in the form of lift jets or lift fans. A brief outline of extensive experience with lift jets, thrust vectoring, and lift fans is given and the importance of this background in making it possible to design more advanced engines which will satisfactorily meet practical operational requirements is brought out. Experience in two generations of lift-jet flight testing has shown many important areas where specal features must be incorporated in the design from the beginning to achieve high thrust for a compact volume, light weight, and high integrity in the relatively severe environment in which the lift jet has to operate. Examples are cited. The relative importance of thrust/volume and thrust/weight ratio is shown with reference to VTOL strike and transport aircraft. An integrated concept, using compact lift jets for VTOL strike aircraft and compact low-efflux-velocity lift fans using the same engine as a gas generator, is briefly noted.

Lift Turbo-fans

1965 ◽  
Vol 69 (656) ◽  
pp. 553-566 ◽  
Author(s):  
C. L. Wilde ◽  
J. F. Coplin
Keyword(s):  
Fuel Consumption ◽  
Weight Ratio ◽  
Jet Noise ◽  
Gas Generator ◽  
The Past ◽  
Gas Generators ◽  
Vectored Thrust ◽  
Vtol Aircraft ◽  
Practical Demonstration ◽  
Efflux Velocity

Summary:In the past decade many powerplant systems have been proposed for VTOL aircraft. Of these, flight tests have shown the lift jet and vectored thrust engine to be practical and suitable for forming the basis of operational VTOL military strike aircraft. High on the list of proposed VTOL powerplant systems is the lift turbo-fan which has the inherent advantages of better hover fuel consumption, lower efflux velocity and lower jet noise. So far there has been no practical demonstration of this type of powerplant in Europe, and it is useful to look at some of the studies that have been made to compare the characteristics of the lift fan and the lift jet.The paper compares the Rolls-Royce RB 162 16:1 thrust/weight ratio lift jet and its installation with a range of Rolls-Royce lift fans derived from the RB 162 using the latter as the gas generator.The comparisons between the basic engines reveal the fan to have worse thrust/volume, thrust/weight and response rates. The installation of these engines in a lift pod is fully described showing the equipment required for complete VTOL powerplant. A comparison of the Installed weight breakdown for the two types of pod is made. Some of the advantage of the fans’ inherently lower fuel consumption is lost in the longer take-off transition time which accrues from the higher momentum drag of the lift fans and higher pod drag.Looking to the future, the authors suggest fan engines based on more advanced gas generators and having a greater degree of ingenuity to minimise the weight and volume penalties.

A novel high thrust–weight ratio linear ultrasonic motor driven by single–phase signal

2018 ◽  
Vol 89 (8) ◽  
pp. 085001 ◽  
Author(s):  
Pingqing Fan ◽  
Xuecheng Shu ◽  
Tao Yuan ◽  
Chaodong Li
Keyword(s):  
Single Phase ◽  
Weight Ratio ◽  
Ultrasonic Motor ◽  
Linear Ultrasonic Motor ◽  
Phase Signal ◽  
High Thrust

A Novel Gas Generator Concept for Jet Engines Using a Rotating Combustion Chamber

2013 ◽  
Author(s):  
Peter Jeschke ◽  
Andreas Penkner
Keyword(s):  
Combustion Chamber ◽  
Weight Ratio ◽  
Thermodynamic Cycle ◽  
Ceramic Materials ◽  
Single Stage ◽  
Jet Engines ◽  
Gas Generator ◽  
Small Core ◽  
Efficiency Increase ◽  
Flow Compressor

A gas generator — consisting of a single-stage shrouded mixed-flow compressor without a diffusor, a rotating combustion chamber, and a vaneless single-stage shrouded centripetal turbine — is presented and analyzed here. All components comprise a coherent rotating device, which avoids most of the problems usually associated with small gas generators. In other words, the concept avoids all radial clearances, it is vaneless, shortens the combustion chamber, minimizes the wetted area and enables ceramic materials to be used, due to compressive blade stresses. However, the concept faces severe structural, thermal and chemical reaction challenges. All these features and their implications are discussed and their benefits for several jet engines are quantified, mainly by means of thermodynamic cycle calculations. An upfront CFD analysis identifies a polytropic compressor efficiency of around 95%. It is then demonstrated that the concept offers a thrust-to-weight ratio which is several times higher than the standard when incorporated into small UAV-type jet engines. It also enables an attractive multistage and dual-flow, but fully vaneless design option. Lastly, a thermal efficiency increase of several percentage points would be achieved, if the concept were to be realized in the (small) core of turbofans with highest overall pressure ratios and high bypass ratios. In summary, the paper presents a gas generator approach which may be considered by designers of small jet engines like those used in UAV applications and it might even be a (challenging) long-term option for the small core engines encountered in future turbofans and turboprops.

Research on a high thrust-to-weight ratio small turbofan engine

1995 ◽  
Author(s):  
Iwao Kashikawa ◽  
Masahiro Akagi ◽  
Satoshi Yashima ◽  
Masataka Ikeyama
Keyword(s):  
Weight Ratio ◽  
Turbofan Engine ◽  
High Thrust

Mobile Compressor Stations for Natural Gas Transmission Service

1967 ◽  
Author(s):  
Trevor Albone
Keyword(s):  
Weight Ratio ◽  
Operating Costs ◽  
Gas Generator ◽  
Hot Gas ◽  
Comparative Cost ◽  
Natural Gas Transmission ◽  
Mobile Compressor ◽  
Aircraft Type ◽  
Base Load ◽  
Maximum Utilization

The paper discusses the development and use of mobile compressor stations to achieve maximum utilization of pipeline facilities by affording protection against outage of base-load compression equipment. The design approach makes use of an aircraft-type turbine as the hot gas generator due to its high power-to-weight ratio and suitability for trailer mounting. Comparative cost data showing the feasibility of the mobile concept are presented, together with details of capital cost and operating, costs. The operating record for two mobile units is outlined, and a program for future operation is presented.

scholarly journals Research of a High Thrust-to-Weight Ratio Small Turbofan Engine

1997 ◽  
Author(s):  
Masahiro Akagi ◽  
Masashi Shinomiya ◽  
Junichi Sakaki ◽  
Shunji Sugai
Keyword(s):  
Research And Development ◽  
Weight Ratio ◽  
Development Program ◽  
Engine Test ◽  
Test Results ◽  
Design Development ◽  
Turbofan Engine ◽  
Technical Research ◽  
Supersonic Aircraft ◽  
High Thrust

The 3rd Research Center of the Technical Research and Development Institute (TRDI) of Japan Defense Agency (JDA) and Ishikawajima-Harima Heavy Industries Co., Ltd. (IHI) developed and tested the demonstrator of a high thrust-to-weight ratio small turbofan engine with an afterburner called “XF3-400”, the purpose of which is to establish engine technologies for the future supersonic aircraft for JDA. The development program started in 1981 and the first engine test was carried out in 1992. All the engine tests planned completed in March 1995 successfully. This paper reports the design, development and test results of the XF3-400 engine above.

On the experimental lead-cooled installation

2020 ◽  
pp. 185-192
Author(s):  
N. V. Aleksandrov ◽  
Ye. D. Blank ◽  
A. D. Kashtanov ◽  
V. V. Stepanov ◽  
V. V. Lemekhov ◽  
...  
Keyword(s):  
Nuclear Power ◽  
Power Plants ◽  
High Efficiency ◽  
High Reliability ◽  
Liquid Lead ◽  
Extensive Experience ◽  
Technical Parameters ◽  
Large Structures ◽  
Speed Up ◽  
Coolant Circulation

Extensive experience in operating nuclear power plants convincingly proves that fast liquid metal cooled reactors are among the most promising. The advantages of using liquid lead coolants in nuclear power industry are shown. In Russia, lately, much attention has been paid to the natural safety of fast reactors. At the stage of testing materials for components of reactor plants, a number of problems arose for basic systems. An experimental lead-cooled installation was developed for testing large structures, continuous monitoring and maintaining specified technical parameters. For reliable coolant circulation (lead coolant circulation speed up to 200 kg/s), a magnetohydrodynamic pump (MHD pump) has been developed, which is distinguished by high efficiency and reliability, it is also ease in operation and maintenance. Currently, the experimental setup is successfully used in scientific research of materials for RU BREST-OD-300. All its systems showed high reliability, maintainability and the possibility of further modernization.

Trajectory Planning for Landing Phase of Reusable Rocket with High Thrust-to-Weight Ratio

2021 ◽  
pp. 5311-5323
Author(s):  
Cong Wang ◽  
Zhengyu Song ◽  
Guoxing Shi ◽  
Qinghai Gong
Keyword(s):  
Trajectory Planning ◽  
Weight Ratio ◽  
High Thrust

A Novel Gas Generator Concept for Jet Engines Using a Rotating Combustion Chamber

2015 ◽  
Vol 137 (7) ◽  
Author(s):  
Peter Jeschke ◽  
Andreas Penkner
Keyword(s):  
Combustion Chamber ◽  
High Efficiency ◽  
Weight Ratio ◽  
Thermodynamic Cycle ◽  
Ceramic Materials ◽  
Single Stage ◽  
Jet Engines ◽  
Gas Generator ◽  
Wetted Area ◽  
Flow Compressor

A gas generator—consisting of a single-stage shrouded mixed-flow compressor without a diffusor, a rotating combustion chamber, and a vaneless single-stage shrouded centripetal turbine—is presented and analyzed here. All components comprise a coherent rotating device, which avoids most of the problems usually associated with small gas generators. In other words, the concept avoids all radial clearances; it is vaneless, shortens the combustion chamber, minimizes the wetted area, and enables ceramic materials to be used, due to compressive blade stresses. However, the concept faces severe structural, thermal, and chemical reaction challenges and is associated with a large Rayleigh-type total pressure loss. All these features and their implications are discussed and their benefits and drawbacks for several jet engines are quantified, mainly by means of thermodynamic cycle calculations. As a result, it has been demonstrated that the concept offers a thrust-to-weight ratio which is higher than the standard when incorporated into small unmanned aerial vehicles (UAV)-type jet engines. It also enables an attractive multistage and dual-flow, but fully vaneless design option. However, the concept leads to a decrease in thermal efficiency if these were to be accomplished in the (small) core of turbofans with highest overall pressure ratios (OPRs) and high bypass ratios. In summary, the paper presents a gas generator approach, which may be considered by designers of small jet engines with high power density requirements, like those used in UAV applications. But this has been proven not to be an option for high-efficiency propulsion.

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