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Record Details

Record 22 of 14549
Thrust chamber thermal barrier coating techniques
Offline Availability: Go to Request Form
Author and Affiliation:
Quentmeyer, Richard J.(NASA Lewis Research Center, Cleveland, OH, United States)
Abstract: Methods for applying thermal barrier coatings to the hot-gas side wall of rocket thrust chambers in order to significantly reduce the heat transfer in high heat flux regions has been the focus of technology efforts for many years. A successful technique developed by NASA-Lewis that starts with the coating on a mandrel and then builds the thrust chamber around it by electroforming appropriate materials is described. This results in a smooth coating with exceptional adherence, as was demonstrated in hot fire rig tests. The low cycle fatigue life of chambers with coatings applied in this manner was increased dramatically compared to uncoated chambers.
Publication Date: Mar 01, 1989
Document ID:
19890013300
(Acquired Nov 06, 1995)
Accession Number: 89N22671
Subject Category: NONMETALLIC MATERIALS
Document Type: Conference Paper
Publication Information: AGARD, Application of Advanced Material for Turbomachinery and Rocket Propulsion; 10 p
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Description: 15p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution within the U.S. granted by agreement
NASA Terms: ELECTROFORMING; FATIGUE LIFE; ROCKET ENGINES; THERMAL BARRIERS (PLASMA CONTROL); THERMAL CYCLING TESTS; THERMAL PROTECTION; THRUST CHAMBERS; HEAT TRANSFER; MANDRELS; MICROCRACKS; PROTECTIVE COATINGS; SURFACE PROPERTIES; THERMAL ANALYSIS; THERMAL DEGRADATION; THERMAL FATIGUE
Imprint And Other Notes: In AGARD, Application of Advanced Material for Turbomachinery and Rocket Propulsion 10 p (SEE N89-22654 16-23)
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