{"id":6735,"date":"2024-09-12T09:34:47","date_gmt":"2024-09-12T09:34:47","guid":{"rendered":"https:\/\/haynesintl.com\/?page_id=6735"},"modified":"2024-09-12T09:34:51","modified_gmt":"2024-09-12T09:34:51","slug":"haynes-230-alloy-for-gas-turbine-aerospace-applications-tech-brief","status":"publish","type":"page","link":"https:\/\/haynesintl.com\/en\/haynes-230-alloy-for-gas-turbine-aerospace-applications-tech-brief\/","title":{"rendered":"HAYNES\u00ae<\/sup> 230\u00ae<\/sup> alloy for Gas Turbine & Aerospace Applications Tech Brief"},"content":{"rendered":"\n

High Performance High-Temperature Expansion Bellows<\/h2>\n\n\n\n

Strength, Stability and Oxidation-Resistance for Gas Turbine and Aerospace Applications to 2100\u00b0F (1150\u00b0C)<\/p>\n\n\n\n

Efficiency-Performance-Cost<\/h3>\n\n\n\n

These three concepts drive future design trends for advanced gas turbine engines and aerospace hardware. HAYNES\u00ae<\/sup> 230\u00ae<\/sup> alloy gives a designer the freedom to meet such challenges “head on”.<\/p>\n\n\n\n

Efficiency<\/h3>\n\n\n\n

Efficiency means “doing more with less”. 230\u00ae<\/sup> alloy has as much as a 50% stress rupture strength advantage over typical workhorse alloys such as HASTELLOY\u00ae<\/sup> X alloy at 1700\u00b0F (925\u00b0C). This opens the door to the use of thinner, more efficient gages.<\/p>\n\n\n\n

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Performance<\/h3>\n\n\n\n

Performance means long-term trouble-free component life and ease of repair. 230\u00ae<\/sup> alloy has the oxidation-resistance to take sustained operation up to 2100\u00b0F (1150\u00b0C) without serious degradation. It also has excellent resistance to microstructural changes in service that should make it readily repairable without need for prior solution annealing. As for cost, 230\u00ae<\/sup> alloy was designed without cobalt, an expensive and import-dependent element. So appreciable savings are available compared to cobalt-containing alloys, such as HAYNES\u00ae<\/sup> 188 alloy.<\/p>\n\n\n\n

Oxidation in Combustion Gases<\/h3>\n\n\n\n

Burner rig dynamic oxidation tests rankings for 2000\u00b0F (1095\u00b0C)\/500 hours exposure to products of combustion of a mixture of No. 1 and No. 2 fuel oil burned at a ratio of air-to-fuel of about 50:1 are shown below. Gas velocity was about 0.3 mach. Samples were automatically removed from gas stream every 30 minutes and fan-cooled to less than 500\u00b0F (260\u00b0C) before reinsertion into the flame tunnel. Maximum metal affected is the sum of the metal loss plus the single deepest point of internal penetration.<\/p>\n\n\n\n

Oxidation Damage<\/h3>\n\n\n\n
\n \n\n \n \n \n \n \n
\n Material <\/td>\n \n Metal Loss <\/td>\n \n Average Metal Loss <\/td>\n \n Maximum Metal Loss <\/td>\n <\/tr>\n
\n \u2013 <\/td>\n \n mils <\/td>\n \n \u00b5m <\/td>\n \n mils <\/td>\n \n \u00b5m <\/td>\n \n mils <\/td>\n \n \u00b5m <\/td>\n <\/tr>\n
\n 230\u00ae<\/sup> <\/td>\n \n 2.2 <\/td>\n \n 5.6 <\/td>\n \n 5.2 <\/td>\n \n 132 <\/td>\n \n 5.7 <\/td>\n \n 145 <\/td>\n <\/tr>\n
\n 188 <\/td>\n \n 7.5 <\/td>\n \n 190 <\/td>\n \n 9.8 <\/td>\n \n 249 <\/td>\n \n 10.7 <\/td>\n \n 272 <\/td>\n <\/tr>\n
\n X <\/td>\n \n 9.0 <\/td>\n \n 229 <\/td>\n \n 12.9 <\/td>\n \n 328 <\/td>\n \n 13.5 <\/td>\n \n 343 <\/td>\n <\/tr>\n <\/table>\n<\/div>