High temperature titanium alloy has the advantages of high specific strength, high temperature resistance, creep resistance, and good fatigue performance. It is an important structural material for key components such as aero-engine disk parts and blades. At the same time, compared with aluminum and magnesium light alloys, titanium alloys have excellent high temperature performance, and thus have considerable application potential in aero-engine high temperature resistant parts. Conventional near-α type high-temperature titanium alloys have difficulty in coordinating heat and thermal stability, a sharp drop in high-temperature oxidation resistance, and a titanium fire problem in local components. According to the design idea of traditional near–α–type Ti–Al–Sn–Zr–Mo–Si hightemperature titanium alloy, the trace elements Er and Re were added respectively, and Ti–6.5Al–2.5Sn–9Zr–0.5Mo–1Nb–1W–0.25Si–0.1Er and Ti–6.5Al–2.5Sn–9Zr–0.5Mo–1Nb–1W–0.25Si–0.1Re two kinds of high temperature resistant titanium alloys for 650℃ with independent intellectual property rights were designed. The best matching mode for thermal strength, thermal stability and creep resistance is sought from the perspective of regulating the thermal processing process and optimizing the heat treatment system. It provides experimental and theoretical basis for the application of high temperature titanium alloy in the aerospace industry.