A research on gas turbine engine operability boundary

Many potential approaches and technologies for reducing CO2 emissions through the use of advanced propulsion and energy systems are not included here in the four high-priority approaches or their associated high-priority research projects. The gas turbine engine 10 is in the form of a high bypass ratio turbofan engine mounted within a nacelle assembly 26, in which most of the air pressurized by the fan section 14 bypasses the core engine itself for the generation of propulsion thrust.

NASA would contribute primarily by supporting basic and applied research in all four approaches, though it would likely play a lesser role in SAJF development given that much of the research e. Enabling higher operating temperatures is a prerequisite to achieving significant improvement in gas turbine engine thermodynamic efficiency, and a major impediment to achieving higher operating temperatures is the difficulty of developing advanced materials and coatings that can withstand higher engine operating temperatures.

Federal Aviation Administration and other certification authorities such as the U. This project aims to identify performance limiting flow mechanisms in a centrifugal compressor stage, with a special interest in the diffuser and its influence upstream and downstream, and to describe the causal relationships between these mechanisms and compressor performance efficiency, pressure rise capability, and operable range.

The objective is to quantify the uncertainty in the D8 benefit, and establish the potential for use in future aircraft designs. To gain insight, unsteady 3-D RANS calculations were carried out on the isolated diffuser using an inlet flow field derived from full stage calculations.

The penalty for encasing the propulsor in a duct is an increase in weight and drag.

Looking for other ways to read this?

Therefore, at a given level of engine, nacelle, and aircraft technology, there is an optimum fan diameter for minimum fuel burn. The work is funded by Pratt and Whitney. Spakovszky Axial inducers are often used in high performance turbopumps for rocket engines in order to reduce system weight and cost.

A key issue is how to address higher distribution voltages designed for operation at altitude. Three sets of bearing rig tests are currently planned. The hot combustion gases flow downstream through turbine stages and extract energy from the gas.

Research infrastructure for electrical technologies. The research and development of megawatt-class turboelectric aircraft propulsion systems is hampered by the lack of development testing facilities. However, the parametric A research on gas turbine engine operability boundary of efficiency on the nature of the waves non-dimensional amplitude and wavelength is currently not well defined, and there may be an opportunity to achieve an enhanced performance through achieving tighter tolerances on surface geometry.

In another example, shown in Figure 7, the outlet 54 of the bleed passage 50 includes a flap assembly which is pivotable about the outlet 54 to control the amount of bleed airflow F3 introduced at the inlet lip section Page 7 Share Cite Suggested Citation: Gas Turbine Engines Low-Pressure-Ratio Fan Propulsors This project would develop low-pressure-ratio fan propulsors to improve turbofan propulsive efficiency.

Currently achievable refinery-gate feedstock prices are expensive relative to the final product, which is driven in part by immature or nonexistent feedstock supply chains.

Work has also been initiated to examine the effects of rotor stator interaction on blade row stalling behavior. Improved aircraft efficiency means that smaller engine cores would be needed since less power would be required for the same mission.

A Methodology for Centrifugal Compressor Stability Prediction Although centrifugal compressors exhibit the same type of instabilities as axial compressors, rotating stall and surge are characterized by a much broader spectrum of unstable behavior.

Thus another objective is to identify the efficiency limiting flow processes when the turbine is subjected to the pulsating flow environment representative of turbocharger twin scroll turbine operation.

Hydrogen is needed for almost all SAJF production, and in several conversion processes those with potentially the lowest feedstock costs it represents a significant portion of operating cost.

Kilohertz laser imaging methods formaldehyde, OH PLIF and PIV are being applied to visualize the unsteady, dynamic interactions between flames and turbulent eddies in the distributed reaction regime.

In another example, the operability condition includes a climb condition. Renewable Fuel Standard program and the Roundtable on Sustainable Biomaterials have established the need for advanced fuels to achieve at least a 50 percent reduction in life-cycle CO2 emissions.

One key research topic is thermal management, because thermal management systems are essential to the performance of the electric propulsion system and because they may affect aircraft flight performance.

A balanced technology investment portfolio in aircraft—propulsion integration research is needed to ensure that economic uncertainties arising from changes in net fuel price do not slow continued reductions in emissions by commercial aircraft. The rapid rate of the expansion leads to non-equilibrium condensation and the fluid entering a metastable state.

A shock tunnel test facility, numerical simulations and analytical modeling are being exercised to understand and provide design options to alleviate adverse effects that high fuel-air ratio combustion may have on hot-section durability, turbine performance, and pollutant emissions.

In fact, the controller 62 itself can generate the signal to cause the actuation of the valve Micro Bearing Rig Rotordynamics A fundamental enabling technology needed for all the high-power-density micro devices is the ability to spin silicon rotating elements, supporting the turbomachinery and electrical components, at peripheral speeds of several hundred meters per second, over two orders of magnitude faster than silicon rotors have previously achieved.

Fan diameters increase as fan pressure ratios FPR are reduced, and the design of innovative nacelle concepts becomes critical to limit the impact of larger diameter fans on nacelle weight and drag.

Recent/Current Research at the Gas Turbine Laboratory

A number of challenges exist in the design and performance assessment of BLI aircraft configurations. A boundary layer 35 is associated with the inlet lip section More structurally and aerodynamically efficient configurations can help address these challenges.

Sustainable Alternative Jet Fuels SAJF Industry Modeling and Analysis This project would undertake research to enable detailed and comprehensive modeling and analysis of SAJF development efforts and impacts at microscale individual projects and macroscale nationwide or worldwide levels to support the needs of policymakers and industry practitioners.

Looking for other ways to read this?

At supercritical state, fluids exhibit peculiar characteristics:. activity is to address key hypersonic combined-cycle-engine issues: (1) dual integrated inlet operability and boundary over wide range of engine operation and compare to pre- Dynamic simulation model for gas turbine engine NASA.

Recent/Current Research at the Gas Turbine Laboratory A Unified Approach for Vaned Diffuser Design in Advanced Centrifugal Compressors. Ruhou Gao. Yuntao is completing his Ph.D. thesis research on the subject of understanding combustion instabilities in a model gas turbine combustor.

The jet engine industry now uses premixed devices in order to reduce pollutants but they can experience "growl" instabilities. Gas turbine engine research. Key research topics for this project include internal and external aerodynamics, acoustics, thrust reversing, operability, manufacturing, and overall weight.

Boundary Layer Ingestion. Washington, DC: The National Academies Press. doi: / The object of research used in this study is a miniature gas turbine engine GTM, which is mainly used as an UAV propulsion system.

The combustion chamber of this engine has a typical, for miniature gas turbines, “quasi-reversed” flow combustion chamber (Fig. 2).

Recent/Current Research at the Gas Turbine Laboratory

A Research on Gas Turbine Engine Operability Boundary. words. 3 pages. Airline Safety and the Reasons of Airplane Crashes. 1, words. 2 pages. A Study on Black Holes. 3, words. 4 pages.

An Overview of Black Holes.

There was a problem providing the content you requested

words. 1 page. A Study on Black Holes Being the .

A research on gas turbine engine operability boundary
Rated 5/5 based on 3 review