Combustion chamber construction

A combustion chamber for use in gas turbines engines, the chamber comprising:

• an inlet for receiving air and fuel to be burned;
• an outlet for expelling products of combustion;
• high strength structural frame means disposed between the inlet and the outlet for supporting mechanical forces associated with the chamber;
• liner means cooperating with the frame means and defining a combustion zone, said liner means including a plurality of panels of high temperature material;
• and
• axial mounting means for positioning said panels axially with respect to said frame means, said axial mounting means including:
• first shoulder means cooperating with preselected of said panels and partially defining a circumferential slot of first predetermined axial width therein;
• and
• second shoulder means cooperating with the frame means, wherein:
• said second shoulder means includes a first flange for disposition within said slot, said first flange having a predetermined second axial width less than said first width;
• and
• said first shoulder means includes a second flange for overlying and retaining the first flange within the slot.

A combustion chamber for use in gas turbine engines, the chamber comprising:

• an inlet for receiving air and fuel to be burned;
• an outlet for expelling products of combustion;
• high strength structural frame means disposed between the inlet and the outlet for supporting mechanical forces associated with the chamber;
• liner means cooperating with the frame means and defining a combustion zone, said liner means including a plurality of panels of high temperature material;
• and
• axial mounting means for positioning said panels axially with respect to said frame means, said axial mounting means including:
• first shoulder means cooperating with preselected of said panels;
• and
• second shoulder means cooperating with the frame means and engaging the first shoulder means, wherein:
• said panels include leading and trailing edges, and preselected of said panels include edge flanges proximate their trailing edges for retaining cooperation with the leading edges of other preselected panels.

A combustion chamber for use in gas turbine engines, the chamber comprising:

• an inlet for receiving air and fuel to be burned;
• an outlet for expelling products of combustion;
• high strength structural frame means disposed between the inlet and outlet for supporting mechanical forces associated with the chamber;
• liner means cooperating with the frame means and defining a combustion zone, said liner means including a plurality of circumferentially segmented panels, said panels adapted for disposition in lateral cooperation to form an annular body;
• axial mounting mans for positioning said panels axially with respect to said frame means;
• and
• a plurality of seals disposed between preselected laterally adjacent panels;
• and wherein said preselected panels include recesses along opposed edges for receiving said seals.