Gas turbine engine including flow turning combustor

A gas turbine engine, comprising:

• a compressor section, a combustion section, and a turbine section, with the combustion section including:
• a flow turning combustor comprising:
• a combustor liner that at least partially defines a combustion chamber including:
• a combustor inlet having an inlet height,
• a combustor outlet having an outlet height and fluidly coupled with the turbine section,
• a primary section extending from the combustor inlet and including a primary length, and
• a transition section extending from the primary section to the combustor outlet and defining a turn;
• a hydrogen fuel supply;
• and
• a fuel nozzle assembly fluidly coupled with the hydrogen fuel supply and the combustor inlet;
• wherein the flow turning combustor defines a combustor centerline extending from the combustor inlet to the combustor outlet, and includes a combustor length measured along the combustor centerline from the combustor inlet to the combustor outlet;
• and
• wherein a ratio of a first product of the combustor length and the outlet height to a second product of the inlet height and the primary length is at least 2.