US 8864492 B2 abstract a reverse flow combustor has an inlet end a flowpath extends downstream from the inlet end through a turn the turn directs the flowpath radially inward and reversing an axial flow direction a large exit duct is along the turn a small exit duct is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction the joint comprises a first surface on the sed facing partially radially inward and a mounting feature engaging the first surface application_number US 201113167167 A description fig1 shows a gas turbine engine 10 generally comprising in serial flow communication from upstream to downstream a fan 12 through which ambient air is propelled a multistage compressor 14 for pressurizing the air an annular reverse flow combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases and a turbine section 18 for extracting energy from the combustion gases the terms axial and radial as used herein are intended to be defined relative to the main central longitudinally extending engine axis 11 centerline further when referring to the combustor 16 herein the terms upstream and downstream and intended to be defined relative to the general flow of air and hot combustion gases in the combustor i e from a fuel nozzle end of the combustor where fuel and air are injected for ignition to a combustor exit where the combustion gases exit toward the downstream first turbine stage referring to fig2 the annular reverse flow combustor.