Double dome combustor

For a gas turbine engine having a compressor providing compressed airflow, a double annular combustor comprising:

• an outer liner;
• an inner liner spaced from said outer liner;
• an outer annular combustor including;
• a first dome having an outer end fixedly joined to said outer liner, an inner end spaced from said outer end, and a plurality of circumferentially spaced first holes disposed therein;
• an inner annular combustor including;
• a second dome spaced from said first dome and having an outer end, an inner end spaced from said second dome outer end and fixedly joined to said inner liner, and a plurality of circumferentially spaced second holes disposed therein;
• said outer and inner liners defining therebetween first and second combustion zones disposed downstream of said first and second domes, respectively;
• and
• means for joining together said first dome and said second dome by two load transmitting structural paths for providing rigidity of said first and second domes for accommodating pressure loading from said compressed airflow.