Gas turbine engine having cooling systems

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section defining a compressor discharge cavity, and a turbine section collectively defining in part a working gas flowpath, the turbomachine further comprising;
• a reverse bleed system comprising a reverse bleed duct and a reverse bleed system (RBS) blower in fluid communication with the reverse bleed duct, the reverse bleed duct in fluid communication with the working gas flowpath;
• and
• an active clearance control (ACC) system comprising an inlet, a heat transfer assembly arranged around a turbine of the turbine section, and an ACC duct assembly extending from the inlet to the heat transfer assembly, the inlet of the ACC system in fluid communication with the reverse bleed duct;
• wherein the turbine is a first turbine and wherein the heat transfer assembly is a first heat transfer assembly, wherein the turbine section further comprises a second turbine and wherein the ACC system further comprises a second heat transfer assembly arranged around the second turbine, wherein the ACC duct assembly extends to both the first heat transfer assembly and the second heat transfer assembly,
• wherein the ACC duct assembly comprises a first portion that extends to the first heat transfer assembly, a second portion that extends to the second heat transfer assembly, and an upstream portion that extends from the inlet of the ACC system to the first portion and the second portion.