Combustor for a gas turbine engine

A gas turbine engine comprising:

• a compressor for compressing air flowing therethrough to provide a compressed air flow;
• a combustor including:
• a dome structure having an outer dome portion and an inner dome portion;
• a cowl structure having an outer cowl portion and an inner cowl portion, the cowl structure connected with the dome structure via an outer connection and via an inner connection;
• an outer liner having an outer liner first end connected to the outer dome portion and the outer cowl portion at the outer connection and an outer liner second end arranged downstream of the outer liner first end;
• an inner liner having an inner liner first end connected to the inner dome portion and the inner cowl portion at the inner connection and an inner liner second end arranged downstream of the inner liner first end, the inner liner, the outer liner, and the dome structure defining a combustion chamber therebetween, the combustion chamber operable to combust an air-fuel mixture to generate combustion products;
• an outer piston ring assembly including an outer piston ring housing having an outer piston ring housing first end connected with the outer connection, and an outer piston ring housing second end arranged downstream of the outer piston ring housing first end, the outer piston ring housing second end including an outer piston ring that engages with an outer side of the outer liner second end;
• and
• an inner piston ring assembly including an inner piston ring housing having an inner piston ring housing first end connected with the inner connection, and an inner piston ring housing second end arranged downstream of the inner piston ring housing first end, the inner piston ring housing second end including an inner piston ring that engages with an inner side of the inner liner second end;
• and
• a turbine section having at least one turbine driven by the combustion products from the combustor.