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Su-24 - Titanium Fires

The first production aircraft was equipped with engine AL-21F (Vol. 85) with a thrust of 87.3 kN in afterburner. One of the features of this engine has been the use of titanium in the compressor with supersonic input stage. A typical disadvantage of this compressor, gas-dynamic characteristics of which were very good, were so-called "titanium" fires.

Upon delivery of the first production aircraft titanium fire broke out due to the fact that the compressor blades were extended under the influence of stress on the body and struck. In place of touch and temperature immediately jumped in conditions of excess oxygen (for he and compressor) metal broke. When the temperature reached the combustion of titanium 3000 C, and this has led to the rapid destruction of the aircraft.

To solve the problem, it was proposed to use a twin-shaft turbojet engines R-29B-Z00 MiG-23, offered an export version of the Su-17M2 (Su-22). This could speed up the process of creating a special modification of the Su-24 for deliveries abroad. Deliveries of the AL-21F were then strictly forbidden, apparently because of his "trophy" pedigree - as is known, a great influence on the birth of the Turbojet was the American J79 received from Vietnam. In 1974 it passed the test aircraft T6-1-8D equipped with a variant of P-29T-ZOO ("T" for -komplektatsiya aircraft T-6). But the worst characteristics of the fuel consumption forced a focus on fine-tuning the costly AL-21F.

When the cause of titanium fires was established , it became a serious problem when testing the aircraft S-32M (Su-17M) (CB "Saturn" redesigned compressor. The weight and size of the engine rose slightly, but its reliability and thrust also increased significantly. After the test T6-3 Su-24 began to equip with modified engines AL-21F-3 (article 89), and then the AL-21F-IN (unified with Su-17M) and AL-21F-ZAT (option for aircraft T-6 minor assembly differences).




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