Innovative High-Temperature Aircraft Engine Fuel Nozzle Design

1993 ◽  
Vol 115 (3) ◽  
pp. 439-446 ◽  
Author(s):  
R. W. Stickles ◽  
W. J. Dodds ◽  
T. R. Koblish ◽  
J. Sager ◽  
S. Clouser
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Surface Finish ◽  
Thermal Protection ◽  
Aircraft Engine ◽  
Engine Fuel ◽  
Sample Tube ◽  
Current Production ◽  
Fuel Nozzle ◽  
A Current

The objective of the Innovative High-Temperature Aircraft Engine Fuel Nozzle Program was to design and evaluate a nozzle capable of operating at a combustor inlet air temperature of 1600°F (1144 K) and a fuel temperature of 350°F (450 K). The nozzle was designed to meet the same performance requirements and fit within the size envelope of a current production F404 dual orifice fuel nozzle. The design approach was to use improved thermal protection and fuel passage geometry in combination with fuel passage surface treatment to minimize coking at these extreme fuel and air temperatures. Heat transfer models of several fuel injector concepts were used to optimize the thermal protection, while a series of sample tube coking tests were run to evaluate the effect of surface finish, coatings, and tube material on the coking rate. Based on heat transfer analysis, additional air gaps, reduced fuel passage flow area, and ceramic tip components reduced local fuel wetted wall temperatures by more than 200°F (110 K) when compared to a current production F404 fuel nozzle. Sample tube coking test results showed the importance of surface finish on the fuel coking rate. Therefore, a 1 μin. (0.025 μm) roughness was specified for all fuel passage surfaces. A novel flow divider valve in the tip was also employed to reduce weight, allow room for additional thermal protection, and provide back pressure to reduce the risk of fuel vaporization. Phase II of this program will evaluate the fuel nozzle with a series of contaminated fuel and coking tests.

Innovative High Temperature Aircraft Engine Fuel Nozzle Design

1992 ◽  
Author(s):  
R. W. Stickles ◽  
W. J. Dodds ◽  
T. R. Koblish ◽  
J. Sager ◽  
S. Clouser
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Surface Finish ◽  
Thermal Protection ◽  
Aircraft Engine ◽  
Engine Fuel ◽  
Sample Tube ◽  
Current Production ◽  
Fuel Nozzle ◽  
A Current

The objective of the Innovative High Temperature Aircraft Engine Fuel Nozzle Program was to design and evaluate a nozzle capable of operating at a combustor inlet air temperature of 1600°F (1144°K) and a fuel temperature of 350°F (450°K). The nozzle was designed to meet the same performance requirements and fit within the size envelope of a current production F404 dual orifice fuel nozzle. The design approach was to use improved thermal protection and fuel passage geometry in combination with fuel passage surface treatment to minimize coking at these extreme fuel and air temperatures. Heat transfer models of several fuel injector concepts were used to optimize the thermal protection, while a series of sample tube coking tests were run to evaluate the effect of surface finish, coatings and tube material on the coking rate. Based on heat transfer analysis, additional air gaps, reduced fuel passage flow area and ceramic tip components reduced local fuel wetted wall temperatures by more than 200°F (110°K) when compared to a current production F404 fuel nozzle. Sample tube coking test results showed the importance of surface finish on the fuel coking rate. Therefore, a 1 micro-inch (.025 micron) roughness was specified for all fuel passage surfaces. A novel flow divider valve in the tip was also employed to reduce weight, allow room for additional thermal protection, and provide back pressure to reduce the risk of fuel vaporization. Phase II of this program will evaluate the fuel nozzle with a series of contaminated fuel and coking tests.

scholarly journals A Parametrical Study on Convective Heat Transfer between High-Temperature Gas and Regenerative Cooling Panel

Energies ◽  
2021 ◽  
Vol 14 (6) ◽  
pp. 1784
Author(s):  
Jiangyu Hu ◽  
Ning Wang ◽  
Jin Zhou ◽  
Yu Pan
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
High Temperature ◽  
Thermal Protection ◽  
Flow Direction ◽  
Heated Surface ◽  
Heat Transfer Process ◽  
Cocurrent Flow ◽  
Regenerative Cooling ◽  
High Temperature Gas

Thermal protection is still one of the key challenges for successful scramjet operations. In this study, the three-dimensional coupled heat transfer between high-temperature gas and regenerative cooling panel with kerosene of supercritical pressure flowing in the cooling channels was numerically investigated to reveal the fundamental characteristics of regenerative cooling as well as its influencing factors. The SST k-ω turbulence model with low-Reynolds-number correction provided by the pressure-based solver of Fluent 19.2 is adopted for simulation. It was found that the heat flux of the gas heated surface is in the order of 106 W/m2, and it declines along the flow direction of gas due to the development of boundary layer. Compared with cocurrent flow, the temperature peak of the gas heated surface in counter flow is much higher. The temperature and heat flux of the gas heated surface both rises with the static pressure and total temperature of gas. The heat flux of the gas heated surface increases with the mass flow rate of kerosene, and it hardly changes with the pressure of kerosene. Results herein could help to understand the real heat transfer process of regenerative cooling and guide the design of thermal protection systems.

Integrating Producibility and Product Performance Tools Within a Web-Service Environment

2003 ◽  
Author(s):  
Kurt A. Beiter ◽  
Kosuke Ishii
Keyword(s):  
Product Development ◽  
Web Service ◽  
Aircraft Engine ◽  
Performance Model ◽  
Product Performance ◽  
Engine Fuel ◽  
Development Environment ◽  
Service Environment ◽  
Fuel Nozzle ◽  
Software Services

This paper describes the integration of a producibility and product performance tool in a web service environment. First, we provide a background on web services and a review of product development environments that utilize a service-based architecture. Next, the paper describes the implementation of two services—a process capability database coupled with an aircraft engine fuel nozzle performance model. Discussions close addressing the challenges faced in the current software services development environment.

scholarly journals Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

1991 ◽  
Author(s):  
G. D. Myers ◽  
J. P. Armstrong ◽  
C. D. White ◽  
S. Clouser ◽  
R. J. Harvey
Keyword(s):  
High Temperature ◽  
Extreme Environment ◽  
Inlet Temperature ◽  
Engine Fuel ◽  
Air Inlet ◽  
Thermal Barriers ◽  
Surface Temperatures ◽  
Marine Diesel ◽  
Fuel Nozzle ◽  
And Performance

The objective of the Innovative High-Temperature Fuel Nozzle Program was to design, fabricate, and test propulsion engine fuel nozzles capable of performance despite extreme fuel and air inlet temperatures. Although a variety of both passive and active methods for reducing fuel wetted-surface temperatures were studied, simple thermal barriers were found to offer the best combination of operability, cycle flexibility, and performance. A separate nozzle material study examined several nonmetallics and coating schemes for evidence of passivating or catalytic tendencies. Two pilotless airblast nozzles were developed by employing finite-element modeling to optimize thermal barriers in the stem and tip. Operability of these prototypes was compared to a current state-of-the-art piloted, prefilming airblast nozzle, both on the spray bench and through testing in a can-type combustor. The three nozzles were then equipped with internal thermocouples and operated at 1600F air inlet temperature while injecting marine diesel fuel heated to 350F. Measured and predicted internal temperatures as a function of fuel flow rate were compared. Results show that the thermal barrier systems dramatically reduced wetted-surface temperatures and the potential for coke fouling, even in an extreme environment.

On the Role of Radiation in Low Density Silicon Carbide Foams

2012 ◽  
Author(s):  
Charles C. Tseng ◽  
Ruth L. Sikorski ◽  
R. Viskanta ◽  
Ming Y. Chen
Keyword(s):  
Heat Transfer ◽  
Silicon Carbide ◽  
High Temperature ◽  
Thermal Radiation ◽  
Thermal Protection ◽  
Mie Scattering ◽  
Radiative Properties ◽  
Void Space ◽  
Insulation Systems ◽  
Foam Properties

There are a variety of foams that can be used in thermal protection and/or thermal insulation systems. At high temperature (> 1000 K) thermal radiation may be important or dominate heat transfer in a foam; however, studies based on more detailed thermal radiation analysis are limited. In this paper foams are considered to be semitransparent, because radiation can penetrate through the pore (or void) space and/or foam skeleton (ligament), depending on the materials from which the foams are made. Of particular interest of this study is to understand how the properties of foam material such as its density, mean cell size, etc. affect the radiative transfer through silicon carbide (SiC) foams. In the paper, the dimensionless strut diameter is considered an important parameter of foams, and the radiative properties of the foams are analyzed by Mie scattering theory. The attenuation/extinction behavior of SiC foams can be considered as a function of the dimensionless strut diameter of the foam. The results reveal that the foam properties can significantly reduce radiative heat transfer through the high temperature foam used for the thermal protection.

Effect of Radiation on Heat Transfer in Open-Cell Foams at High Temperature

2011 ◽  
Author(s):  
Charles C. Tseng ◽  
Ruth L. Sikorski ◽  
R. Viskanta ◽  
Ming Y. Chen
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Thermal Radiation ◽  
Thermal Protection ◽  
Radiant Energy ◽  
Radiation Absorption ◽  
Solid Matrix ◽  
Void Space ◽  
Insulation Systems ◽  
Physical And Mathematical Models

There are a variety of foams that can be used in thermal protection and/or thermal insulation systems. At high temperature (> 1000 K) thermal radiation may be important or dominate heat transfer in the foam; however, studies based on more detailed thermal radiation analysis are limited. In this paper foams are considered to be semitransparent, because radiation can penetrate through the pore (or void) space and/or foam skeleton (solid matrix), depending on the materials from which the foams are made. Of particular interest of this study is to understand how the properties such as foam material its density, porosity, etc. affect thermal and radiant energy transfer. Physical and mathematical models are developed to account for conduction and radiation (absorption, emission and scattering) in the porous material. The spectral extinction coefficients of SiC foams are measured experimentally in the laboratory at room temperature, and the radiative transfer equation is solved using the spherical harmonics P1 and the Rosseland diffusion approximations. Parametric calculations have been carried out, and the results are reported in the paper for a range of parameters characterizing heat transfer in SiC foams of different porosities to identify desirable conditions for effectively reducing heat transfer in potential thermal protection concepts.

Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

1992 ◽  
Vol 114 (2) ◽  
pp. 401-408 ◽  
Author(s):  
G. D. Myers ◽  
J. P. Armstrong ◽  
C. D. White ◽  
S. Clouser ◽  
R. J. Harvey
Keyword(s):  
High Temperature ◽  
Extreme Environment ◽  
Inlet Temperature ◽  
Engine Fuel ◽  
Air Inlet ◽  
Thermal Barriers ◽  
Surface Temperatures ◽  
Marine Diesel ◽  
Fuel Nozzle ◽  
And Performance

The objective of the innovative high-temperature fuel nozzle program was to design, fabricate, and test propulsion engine fuel nozzles capable of performance despite extreme fuel and air inlet temperatures. Although a variety of both passive and active methods for reducing fuel wetted-surface temperatures were studied, simple thermal barriers were found to offer the best combination of operability, cycle flexibility, and performance. A separate nozzle material study examined several nonmetallics and coating schemes for evidence of passivating or catalytic tendencies. Two pilotless airblast nozzles were developed by employing finite-element modeling to optimize thermal barriers in the stem and tip. Operability of these prototypes was compared to a current state-of-the art piloted, prefliming airblast nozzle, both on the spray bench and through testing in a can-type combustor. The three nozzles were then equipped with internal thermocouples and operated at 1600°F air inlet temperature while injecting marine diesel fuel heated to 350°F. Measured and predicted internal temperatures as a function of fuel flow rate were compared. Results show that the thermal barrier systems dramatically reduced wetted-surface temperatures and the potential for coke fouling, even in an extreme environment.

Significance of Solar Radiation on Aircraft Engine Under Cowl Temperature

2007 ◽  
Author(s):  
A. R. Abu Talib ◽  
A. A. Jaafar ◽  
A. S. Mokhtar ◽  
A. H. Razali
Keyword(s):  
Heat Transfer ◽  
Solar Radiation ◽  
Convective Heat Transfer ◽  
Convective Heat ◽  
Surface Finish ◽  
Experimental Work ◽  
Radiation Effect ◽  
Aircraft Engine ◽  
Temperature Distributions ◽  
Engine Nacelle

Literature on solar radiation effect on aircraft engine under cowl temperature is very limited. This paper describes an experimental work to quantify the effect of solar radiation levels on a range of aircraft engine nacelle surface finish and orientation in a representative way. The investigation was carried out on four aircraft engine nacelle representations during static ground running conditions. The nacelle models were fabricated using aluminium and surface coated with four different aircraft paint finish. Thermocouples were mounted at locations around the nacelle model. Effects of different solar radiation levels on the temperature distributions on the nacelles were presented. The contributions of radiative and convective heat transfer on the overall distribution of temperature inside the under cowl were quantified.

Analytical Solution Under Two-Flux Approximation to Radiative Heat Transfer in Absorbing Emitting and Anisotropically Scattering Medium

2010 ◽  
Vol 132 (12) ◽  
Author(s):  
Xin-Lin Xia ◽  
Dong-Hui Li ◽  
Feng-Xian Sun
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Radiative Transfer ◽  
Analytical Solution ◽  
Radiative Heat Transfer ◽  
Radiative Heat ◽  
Thermal Protection ◽  
Isotropic Scattering ◽  
Scattering Media ◽  
Flux Approximation

Radiative transfer in absorbing, emitting, and highly anisotropically scattering media is widely encountered in high temperature applications such as pulverized coal firing furnaces and high temperature thermal protection materials. Efficient and effective solution methods for the transfer process are very crucial, especially in thermal radiation related reverse problems and optimization designs. In this study, the analytical solution for radiative heat transfer in an absorbing, emitting, and anisotropically scattering slab between two parallel gray walls are derived under the two-flux approximation. Explicit expression for the radiative heat flux in a slab is obtained under two-flux approximation. The reliability and adaptability of an analytical solution is examined in case studies by comparing with the Monte Carlo results. Comparative studies indicate that the analytical solution can be used in radiative transfer calculation in an absorbing emitting and anisotropically scattering slab. It is much more applicable in a forward and isotropic scattering slab than in an absorbing one, especially in a forward scattering slab. Because of simplicity and high computing efficiency with the analytical solution, it may be useful in reverse radiative transfer problems, in optimization design, and in developing some numerical schemes on radiative heat transfer.

Research on Thermal Protection of One Gas Generator

2014 ◽  
Vol 945-949 ◽  
pp. 1050-1053
Author(s):  
Zong Zheng Liu ◽  
Bo Zhao ◽  
Zhen Hua Chen ◽  
Cheng Guo Yu
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Thermal Protection ◽  
Gas Generator ◽  
Protection Measures ◽  
Key Factor ◽  
Time Position ◽  
High Temperature Condition ◽  
Simulation Results ◽  
Numeral Simulation

The thermal protection is a key factor to keep the gas generator work longtime under high temperature condition steadily. The main heat transfer paths are analyzed. A numeral simulation of the combustor and its nozzle shows the pipe outside temperature distribution with the change of time, position and thickness. According to the numeral simulation results, two thermal protection measures are bring forward, reduce the temperature, choosing proper thickness and heat resisting material. At last, an experiment results validate that the numeral simulation is credibility; the improvement of the structure is effective. With a longtime run, the outside wall temperature is 870K, which satisfies the operation needs.

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