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Abstract:

Heat-resistant alloys are arbitrarily defined as iron alloys richer in alloy content than the 18 percent chromium, 8 percent nickel types, or as alloys with a base element other than iron and which are intended for elevated-temperature service. These alloys have adequate oxidation resistance for service at elevated temperatures and are normally used without special surface protection. So-called 'refractory' alloys that require special surface protection for elevated-temperature service are not included in this chapter.

This chapter contains strength properties and related characteristics of wrought heat-resistant alloy products used in aerospace vehicles. The strength properties are those commonly used in structural design, such as tension, compression, bearing, and shear. The effects of elevated temperature are presented. Factors such as metallurgical considerations influencing the selection of metals are included in comments preceding the specific properties of each alloy or alloy group. Data on creep, stress-rupture, and fatigue strength, as well as crack-growth characteristics, are presented in the applicable alloy section.

See also:

• MMPDS: CHAPTER 1 - INTRODUCTION
• MMPDS: CHAPTER 2 - STEEL ALLOYS
• MMPDS: CHAPTER 3A - ALUMINUM ALLOYS - General through 2000 Series
• MMPDS: CHAPTER 3B - ALUMINUM ALLOYS - 3000 through 7000 Series
• MMPDS: CHAPTER 3C - ALUMINUM ALLOYS - Cast Alloys and Element Properties
• MMPDS: CHAPTER 4 - MAGNESIUM ALLOYS
• MMPDS: CHAPTER 5 - TITANIUM ALLOYS
• MMPDS: CHAPTER 6 - HEAT-RESISTANT ALLOYS (this Chapter)
• MMPDS: CHAPTER 7 - MISCELLANEOUS ALLOYS AND HYBRID MATERIALS
• MMPDS: CHAPTER 8 - STRUCTURAL JOINTS
• MMPDS: CHAPTER 9 - GUIDELINES
• MMPDS: APPENDICES A-E