A research on gas turbine engine operability boundary

Derek's research interests focus on the propulsion systems and flight dynamics of air-breathing hypersonic vehicles. In some cases, the propagation frequency can approach the rotor shaft natural frequency, which can cause severe vibrations that present a significant risk to the turbopump.

Federal Aviation Administration and other certification authorities such as the U. This research had an engineering objective to find better ways of building compact, lightweight high pressure vessels for demanding applications such as spacecraft. The Dynamics of Turbulent Premixed Flames: Robin Klomparens Robin joined Michigan after completing undergraduate studies at the University of Maryland; she has been awarded a prestigious NSF fellowship.

The dynamic cavitation behavior is often unsteady and periodic, leading to several distinct cavitation instabilities. A converging-diverging nozzle with characteristic through-flow times and length scales similar to those of the compressor was chosen as a test case.

The approach exploits a recently developed body-force based modeling approach that has been used successfully in aerodynamic instability modeling of jet engine axial and centrifugal compressors as well as in acoustic descriptions of non-uniform flow in transonic fans.

Understanding of these drivers would allow the formulation of strategies for turbine performance and durability enhancement to benefit the next generation of large industrial gas turbines for power generation. A current topic under investigation is the effect film cooling on aerodynamic performance and heat transfer.

The second aspect seeks to quantify the variation of efficiency as blade rotor tip and stator hub clearance approaches zero and its implication on peak efficiency in a multistage environment.

Requirements for electrical system components are beyond the current state of the art, especially for large commercial aircraft. Several proposed advanced aircraft designs include configurations in which the boundary layer developing along the aircraft is ingested into the propulsor resulting in wake cancellation, which reduces the power needed to propel the aircraft and so reduces energy consumption and CO2 emissions.

Gas turbine engine research. This rotor has approximately half the mass of the magnetic rotor, so a solder-filled rotor twice as heavy will be tested next to determine whether the bearings perform well with a massive rotor. Using the developed CRP noise estimation method, the underlying noise mechanisms front-rotor wake interaction, aft-rotor upstream influence, hub-endwall secondary flows, and front-rotor tip-vortices to interaction tone noise are dissected and quantified.

Recent/Current Research at the Gas Turbine Laboratory

The conduit section 58 extends within a cavity 63 within the fan cowl 46 of the nacelle assembly The theme of the technical approach is a unique analytical, reduced-order dynamic system modeling methodology, which incorporates a system rather than a component view of this multi-disciplinary problem.

Not all alternative fuels will result in a net reduction in life cycle carbon depending, for example, on their source materials. For a constant level of thrust, this requires that the effective fan area increase so as to avoid commensurate increases in weight, drag, and integration losses.

This research program focuses on the key technical issues relating to the modeling and integration of flow control devices in aero-engine compressors with the goal to further enhance the performance and operability beyond the current loading and stability limits.

The development of feedstocks is one of several technical challenges that must still be overcome to enable economically competitive production of SAJF at scales of significance. Of course, this view is highly schematic. Of course, Figure 5 is a schematic view.

He did two years of his Ph. The devices would be capable of producing watts of power or grams of thrust. Abstract The scope of this study is the experimental and theoretical research into the developed concept of variable geometry combustion chamber for miniature gas turbine engine.

While there is substantive literature on the effects of surface roughness, transonic flows over wavy wall, transition and the generation of turbulence, there is much less information on the effect of blade surface waviness on compressor performance.

These include all-electric and hybrid-electric propulsion systems, high-power batteries and fuel cells for propulsion, superconducting motors and generators, hybrid compound engines which combine a gas turbine and another internal combustion engine such as a dieselengines that use thermodynamic cycles other than the simple Brayton cycle that is used by conventional gas turbine engines, and alternative fuels such as hydrogen or liquefied natural gas.

The Economic Value of Silence Rising congestion and delays throughout the air transport system are in part associated with noise-related operational restrictions and airport expansion delays.

Presently, all the silicon die fabrication is complete, and the magnetic components are being integrated onto the die in preparation for power generation testing. The method as recited in any of claims 15 to 18, wherein said step b comprises the step of: The work is funded by Pratt and Whitney.

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.

High Fuel-Air Ratio Combustor and Turbine Research As temperatures and overall fuel-to-air ratios increase in commercial and military aircraft engines, the potential for significant heat release due to post-combustor oxidation of partially reacted fuel is increased.

The objective is to quantify the uncertainty in the D8 benefit, and establish the potential for use in future aircraft designs. The main area of interest in the compressor is the leading edge of the impeller.

Identification and quantification of key drivers for uncertainty and engine-to-engine variability in aerothermal quality including validation against data; Definition of criteria for the design of engines with a commercially-significant reduction in sensitivity to uncertainty and variability including analysis of cost trade-offs; Development of improved processes for monitoring and controlling the effects of variability on aerothermal quality; Implementation of one or more of the above elements in an industrial setting.

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 existence of an inherent positive pressure gradient may cause the boundary layer separation on compressor blades leading to the rotating stall and surge. Such condition, however, does not exist in a turbine, and operability of the engine. Accurately predicting these stress conditions The gas turbine GT-9 of Brown Boveri used for.

Recent/Current Research at the Gas Turbine Laboratory A Unified Approach for Vaned Diffuser Design in Advanced Centrifugal Compressors.

Ruhou Gao.

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nature of the engine inlets and boundary layer ingestion on engine performance FLOW CONTROL RESEARCH AT NASA GLENN FOR GAS TURBINE ENGINES FLOW CONTROL RESEARCH AT NASA GLENN FOR GAS TURBINE ENGINES Engine Noise Reduction. Flashback Phenomena Associated with Lean Premixed Syngas Combustion at Gas Turbine Like Conditions S.

Daniele1, P. Jansohn1, limits and operability issues of a modern Gas Turbine engine. Dependence on the combustion conditions typical for gas turbine applications.

The boundary layer flashback mechanism is. The use of fl uids within a gas turbine engine defi nes the very function of the boundary layers, separation regions, core fl ows, leakages, injections, and even and the main uses of impingement to maintain the engine function and operability.

While the use of impingement for cooling of the combustor, high-pressure turbine (HPT.

A research on gas turbine engine operability boundary
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