Multi-axial pivoting combustor liner in gas turbine engine

A combustor liner for a gas turbine engine comprising:

• a lower joint that moveably connects said liner with a turbine scroll;
• an upper joint that movably attaches housing to said liner;
• said lower joint and said upper joint providing multiple axes of movement for said liner;
• a vibration damper/thermal and mechanical spring;
• said vibration damper/thermal and mechanical spring providing resiliency to said liner in a first direction from said atomizer to said turbine scroll, thereby maintaining said lower joint in a connected state;
• said vibration damper/thermal and mechanical spring providing resiliency to said liner in a second direction, orthogonal to said first direction, thereby minimizing movement of said liner in said second direction;
• a hole in said liner for inserting an igniter;
• and
• a grommet for moveably holding said igniter in said hole.

A combustor liner for a gas turbine engine of a high performance aircraft comprising:

• a lower joint that moveably connects said liner with a turbine scroll;
• an upper joint that movably attaches housing to said liner;
• said lower joint and said upper joint providing multiple axes of movement for said liner;
• a vibration damper/thermal and mechanical spring;
• said vibration damper/thermal and mechanical spring providing resiliency to said liner in a first direction from said atomizer to said turbine scroll, thereby maintaining said lower joint in a connected state;
• said vibration damper/thermal and mechanical spring providing resiliency to said liner in a second direction, orthogonal to said first direction, thereby minimizing movement of said liner in said second direction;
• a hole in said liner for inserting an igniter;
• a grommet for moveably holding said igniter in said hole;
• a forging ring, said forging ring having a first surface for movably contacting said turbine scroll and a second, opposite surface attached to said liner;
• said first surface forming a substantially spherical point of contact between said liner and said turbine scroll;
• said second surface having a diameter smaller than a diameter of said first surface;
• fine holes in said forging ring;
• an upper joint louver for deflecting air from said upper joint;
• sweep holes in said upper joint, said sweep holes providing cooling for said upper joint;
• a contact angle formed between a liner centerline and said upper joint is optimized to minimize friction force;
• and
• a carbon deflector extending into said combustion zone around said upper joint.

A method for operating a turbine engine, comprising:

• encasing a combustor zone with a combustor liner;
• providing a fuel source via an atomizer to said combustor zone;
• providing an ignition source to said combustor zone;
• and
• passing the combustion gases through a turbine scroll to drive a turbine;
• wherein
• said combustor liner is a multi-axial pivoting liner having a lower joint that moveably connects said liner with said turbine scroll and an upper joint that movably attaches housing to said liner, said lower joint and said upper joint providing multiple axes of movement for said liner, wherein inspection or removal of said atomizer is performed without requiring complete disassembly of said combustor liner.