HEAT SHIELD FOR GAS TURBINE ENGINE Russian patent published in 2021 - IPC F01D11/08 F01D11/24 F01D25/12 F02C7/18 

FIELD: engineering.

SUBSTANCE: heat shield (60) for a gas turbine engine (10) is comprised of a main body (61) with a first surface (70) and a second surface (72), wherein the first surface (70) is exposed to hot working gas during operation, multiple walls (74, 76, 78, 80) extending from the second surface (72) and an impact plate (86). The impact plate (86) is located on top of at least one wall from the multiple walls (74, 76, 78, 80), forms a chamber (88) with the second surface (72) and the multiple walls (74, 76, 78, 80) and comprises a group of impact holes (90). At least one pair of dividing walls (92, 94) comprises a first dividing wall (92) and a second dividing wall (94) formed within the chamber (88) and further extending between the impact plate (86) and the second surface (72). The first dividing wall (92) has a length extending from the first wall (74, 76, 78, 80) from the multiple walls (74, 76, 78, 80) to the second wall (74, 76, 78, 80), wherein the second wall (74, 76, 78, 80) opposes the first wall (74, 76, 78, 80), wherein the second dividing wall (94) has a length extending from the second wall (74, 76, 78, 80) to the first wall (74, 76, 78, 80). The first dividing wall (92) and the second dividing wall (94) both further extend so that there is no clear line of sight perpendicularly (96) to the first dividing wall (92) and/or to the second dividing wall (94), wherein the first dividing wall (92) and the second dividing wall (94) are spaced apart relative to the perpendicular direction.

EFFECT: improved cooling of the gas turbine components reducing temperature gradients, reducing absolute temperatures and minimizing use of cooling air.

16 cl, 5 dwg