Combustors with hybrid walled liners

A combustor for a turbine engine, comprising:

• a first liner;
• a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial, radial and circumferential directions,
• the first liner being a first dual walled liner comprising a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends;
• and
• a first primary air admission hole defined in the first hot wall;
• and
• a first fixed liner seal between the first hot wall and the first cold wall proximate to the primary air admission hole;
• and
• a first sliding liner seal between the first hot wall and the first cold wall on the first end of the first liner cavity.