| 摘要 |
A gas turbine engine includes a compressor section, a combustor, and a turbine section (100). The turbine section (100) includes a first turbine portion (110) and a second turbine portion (120), with the first and second turbine portions (110; 120) being counter-rotating turbine portions. A transition duct (102) transitions fluid flow from the first turbine portion (110) to the second turbine portion (120). The transition duct (102) is a vaneless transition duct. |
