Fuel Tank Heat Shield Design

1990 ◽  
Author(s):  
Colin Jordan ◽  
Dale Matkovich
Keyword(s):  
Fuel Tank ◽  
Heat Shield ◽  
Shield Design

Novel Approach towards Fuel Tank Heat Shield Design

2017 ◽  
Author(s):  
V N Bhasker ◽  
Abhinav Agarwal ◽  
Abhishek Sharma ◽  
Avisek Das ◽  
Nirajkumar Mishra
Keyword(s):  
Fuel Tank ◽  
Heat Shield ◽  
Novel Approach ◽  
Shield Design

INFLUENCE OF MATERIAL PROPERTIES ON RE-ENTRY VEHICLE HEAT SHIELD DESIGN

1967 ◽  
Author(s):  
LEURI HILLBERG
Keyword(s):  
Material Properties ◽  
Heat Shield ◽  
Shield Design

The First Mission of Iranian Spacecraft: Heat Shield Design

2015 ◽  
Vol 8 (4) ◽  
pp. 383-388
Author(s):  
A. Tahsini
Keyword(s):  
Heat Shield ◽  
Shield Design

Design of Heat Shield for Compressor Case of Industrial Gas Turbine to Meet Clearance Requirement

2020 ◽  
Author(s):  
Prashant Malavade ◽  
Santhana G. Babu ◽  
Luca Frosini ◽  
Simone Marchetti
Keyword(s):  
Gas Turbine ◽  
Low Cycle Fatigue ◽  
Operating Conditions ◽  
Heat Shield ◽  
Design Parameters ◽  
Cycle Fatigue ◽  
Excessive Heat ◽  
The Impact ◽  
Shield Design ◽  
Aerodynamic Losses

Abstract In Gas Turbine design key important role was to establish proper clearance between rotating and statoric parts during operating conditions which controls the performance, cooling flow requirements, part performance etc., These clearances must be optimized to meet product requirements. Too tight clearance at assembly condition causes excessive rubbing during starting or shutdown of gas turbine which could cause excessive heat generation and damage rotating and statoric parts. In some case, rubbing can cause tip liberations and damages to flow path causing aero dynamic losses. Similarly, if clearance is large at assembly condition causes aerodynamic losses. In this paper describes the experience of Baker Hughes, in design of compressor case wherein different design options in casing design with and without considering external features / components are considered to have adequate clearance between rotating and statoric parts. It also describes the Heat shield design iterations which was provided on a compressor case to establish proper thermal response during transient operating conditions. This helps in providing adequate clearance without causing excessive rubs or too large clearance avoiding aerodynamic losses. During development of heat shield design, challenges encountered considering clearance, manufacturing aspects, assembly feasibility and part life capabilities like low cycle fatigue, high cycle fatigue requirements are discussed in the paper. Also heat shield was subjected to high thermal gradient due to temperature difference, this makes heat shield to have constrained growth. This restriction in growth provides huge stresses beyond the material limit causing it to fail before product requirement time period. To avoid constrained growth, this paper describes how the heat shield was connected to casing by different means are mentioned. It also describes the impact on frequency margin if there is not adequate fixity in heat shield design. Some of the design parameters like circumferential & axial ribs and intermittent stiffeners and its influence on stress by comparing against yield and on frequency margin with reference to potential driver are also discussed in this paper. It also incorporates the methods to control intersegment leakages and design features to avoid interface interference. Feasibility study of heat shield design was done using finite element modeling techniques using ANSYS tool and its best practices would also be dealt in this paper.

Ablative Heat Shield Design for Reentry Vehicle Using Numerical Analysis

2014 ◽  
Vol 598 ◽  
pp. 298-303
Author(s):  
Amir Mahdi Tahsini ◽  
Samaneh Tadayon Mousavi
Keyword(s):  
Heat Flux ◽  
Heat Shield ◽  
Interface Temperature ◽  
Final Thickness ◽  
Reentry Vehicle ◽  
Simulated Trajectory ◽  
Flux Profile ◽  
Heat Shields ◽  
Energy Equations ◽  
Shield Design

At this paper, the thermal behavior of ablative materials as heat shields for reentry vehicles is investigated numerically. A one-dimensional finite difference solver is developed to simulate governing mass and energy equations. Four ablative materials; AVCO 5026-HCG, Carbon-Phenolic, Nylon-Phenolic, and Silica-Phenolic; are considered as a heat shield material for a reentry capsule with the diameter 2.8 meter. A heat flux profile from a simulated trajectory of a reentry capsule is used for investigation the performance and essential thickness of these four ablative materials. The only restriction for this simulation is the ultimate temperature of the backup structure which is beneath the ablative heat shield. At all simulations, the final thickness is defined by reaching the interface temperature, the temperature of the border between the ablative heat shield and solid shell, to 80±0.5 degrees Celsius. In addition, the sensitivity analysis is carried out to investigate the effect of properties variations on Carbon-Phenolic’s thickness for this specific heat flux profile.

A Multifunctional Approach to Supporting Heat Shield Design and Development

1997 ◽  
Author(s):  
D. R. Bridge ◽  
R. Butler
Keyword(s):  
Heat Shield ◽  
Design And Development ◽  
Shield Design

424. Heat Stress During Fuel Tank Entry and Maintenance Activities on U.S. Air Force and Commercial Aircraft

1999 ◽  
Author(s):  
G. Kinnes ◽  
P. Jensen ◽  
K. Mead ◽  
D. Watkins ◽  
L. Smith ◽  
...  
Keyword(s):  
Heat Stress ◽  
Air Force ◽  
Fuel Tank ◽  
Commercial Aircraft ◽  
Maintenance Activities

Configuration impact on heat shield requirements for Jupiter entry

1976 ◽  
Author(s):  
W. NICOLET ◽  
A. BALAKRISHNAN ◽  
S. MEZINES
Keyword(s):  
Heat Shield

Analysis of Jupiter probe heat shield recession uncertainties

1978 ◽  
Author(s):  
H. NELSON ◽  
S. MEZINES
Keyword(s):  
Heat Shield
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