GAS TURBINE ENGINE, COMBUSTION CHAMBER INNER SHELL FOR GAS TURBINE ENGINE AND ROTOR CASE FOR GAS TURBINE ENGINE Russian patent published in 2016 - IPC F01D9/02 F23R3/60 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine includes a compressor, annular combustion chamber and turbine. Combustion chamber in transition zone of its shell is adjacent to input in turbine to caused by thermal expansion relative movement between combustion chamber and turbine. Shell of combustion chamber with its distributed along perimeter of support elements against due to arising in working mode of thermal expansion in conical path to rotor casing located between compressor outlet and inlet zone of turbine, as well as between rotor and inner shell of combustion chamber, and rests on it. Conical loop forms with the axis of gas turbine engine angle providing sliding shell combustion chamber support elements at conical outline. Another invention of group relates to inner shell of combustion chamber, which at output end facing from hot gases has distributed along perimeter of support elements with skew. Skew of support elements assembled extends parallel with conical outline of rotor casing and forms with axis of gas turbine engine angle providing sliding support elements of inner shell of combustion chamber at conical outline of rotor casing. One more invention relates to rotary casing, which on downstream end of outer side has a conical circuit together with axis of gas turbine engine angle providing combustion chamber inner enclosure sliding support elements at conical outline.

EFFECT: group of inventions increases service life of gas turbine engine due to elimination of wear between combustion chamber and turbine.

15 cl, 5 dwg