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The Combustion Branch conducts fundamental and applied research aimed at advancing the technology
for combustors, combustion processes and emission reduction of aeronautical gas turbine engines
and space propulsion. The research is applicable to high-speed aircraft, rotorcraft, general aviation/commuter
aircraft, subsonic transports and cruise missiles for civil and/or military applications. A range of combustor
types are addressed. The research is focused on providing improved understanding of combustion processes
to include the chemical kinetics of reacting flows, heat transfer phenomena, flow physics modeling
and code development/verification. The advanced computational methods are applied to advanced and
unique concepts to assess their potential. Experiments are conducted to demonstrate proof-of-concept.
Advanced diagnostics are applied in the basic and applied experiments. Advanced high temperature materials,
unique fuels, and low NOx combustion systems are assessed. The work is accomplished through in-house research
grants with universities and contracts with the industries, often in cooperation with other government agencies.
Provides support to other Glenn organizations as needed.
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The fuel injector/mixer is a component of an integrated Jet fuel processor device that we herein refer to as a reformer.
The reformer reactor that the injector operates with is a high temperature catalytic fuel processor designed to convert Jet-A fuel
into a hydrogen-rich synthesis gas for ultimate use in a solid oxide fuel cell (SOFC) for aircraft APU application.
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We are performing a combined experimental and theoretical effort to develop a spectral
calibration database for multi-scalar diagnostics using spontaneous Raman scattering (SRS) in high-pressure flames.
SRS is perhaps the only optical diagnostic technique that can provide single-shot spatially-resolved multi-scalar measurements
of species concentration and temperature in turbulent flames.
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FUELS AND FLAME SPRAY RESEARCH---Text goes here
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Aircrafts emit gases and particles into upper atmosphere and change atmospheric composition.
Specially instrumented aircraft or balloons are necessary to study the effects of emissions on the upper atmosphere.
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COMBINED CYCLED PPROPULSION COMBUSTOR ---Text goes here
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The objective of this project is to develop a combustor concept that reduces gaseous,
particulate, and aerosol emissions. To achieve low emissions it is important to achieve fine atomization
and mixing of the fuel and air quickly and uniformly, so that flame temperatures are low.
The concept described is a multipoint fuel-injection, multi-burning zone concept.
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The advancement made during the last decade in the areas of combustion modeling,
numerical simulation, and massively parallel computing have greatly facilitated the application
of Computational Fluid Dynamics (CFD) based methodology in the development of combustion technology.
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Perform risk reduction research on several of the innovative system components of the Mars Hopper concept
to increase the foundation of the concept and prepare for a potential flight experiment effort
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All-tank, full-time fuel tank inerting to protect against accidental and deliberate fuel tank ignition.
This project seeks to develop more economical gas separation technologies through higher-temperature
hollow-fiber-membrane (HFM) air separation modules (ASM) and combustion derived inerting (CDI)
to reduce aircraft resource requirements. This project also seeks to apply advanced optical gas sensors
(currently under development) in a closed-loop feed-back control system to provide just-enough intelligent
fuel tank protection to minimize taxing aircraft resource as well as minimizing crew attention.
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Metallized gelled rocket propellants have been considered for many different applications.
While operational usage has not yet come to fruition, there are many technology programs
that are underway to eliminate the unknowns with gelled propellants and the propulsion systems
that will use them. Numerous studies have shown the potential benefits of gelled fuels
and oxidizers. Technology programs to prove the combustion performance of gelled propellants
have been conducted most recently by the U.S. Army Missile Command, with their industry and
university partners, for tactical missile applications.
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We are studying hydrogen combustion to demonstrate that hydrogen can be used as an aviation fuel Now
and in the Future. We are trying to minimize emissions at upper troposphere and lower stratosphere.
We are also trying to demonstrate that coking and smoking problems can be eliminated during aircraft operations.
We are studying hydrogen combustion to demonstrate that hydrogen can be used as an aviation fuel Now and in the Future.
We are trying to minimize emissions at upper troposphere and lower stratosphere. We are also trying to demonstrate that coking
and smoking problems can be eliminated during aircraft operations.
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For an engine with an additional burner between the high pressure turbine (HPT station 5)
and the low pressure turbine (LPT station 6), more energy can be added in the engine because
the limiting condition is the maximum metal temperature T4. More heat can be added in the ITB at station 6
because the temperature of the gases are reduced by expansion through the HPT at station 5.
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CEA is a well-known and heavily used FORTRAN program that has been documented
with NASA reports NASA TP-1311, parts I and II. The program calculates
equilibrium compositions and properties with the built-in applications:
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- Advance the state-of-the-art for long-term storage of cryogenic fluids in reduced gravity environments by:
- developing the most promising analytical and numerical models;
- anchoring the models with new or existing test data;
- developing the most promising pressure control concepts through a combination of component and system level testing. (TRL ~ 4); and
- gaining experience with full scale loading/control of potential green propellants for future systems.
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- Alternative Fuels for Next Generation Combustion Applications,
led by Dr. Chi-Ming Lee and Dr. Dan Bulzan of the Combustion Branch, tested Fischer-Tropsch fuels
using the new Pratt & Whitney ultra-high bypass ratio engine. Results have demonstrated,
for the first time, that Fischer-Tropsch (FT) fuels can run in advanced engines with no combustor
or fuel compatibility issues.
- An Alternative Fuel Research Laboratory, funded under
the Fundamental Aeronautics Research Program, is housed within the center's recently remodeled
Heated Tube Facility to conduct alternative fuels testing utilizing the Fisher-Tropsch (FT) process.
Glenn leads NASA's research effort to convert some of the nation's natural energy sources
-- coal, natural gas (methane), biomass and shale oil -- into a cleaner and
more economical alternative to traditional commercial jet fuel.
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