COOLED TURBINE GUIDE BLADE AND TURBINE HAVING SAID BLADES Russian patent published in 2007 - IPC F01D9/02 

FIELD: gas turbine engines.

SUBSTANCE: guide blade of gas turbine engine comprises front and rear edges, pocket, wing back, as well as opened perforated insert, inlet orifice to supply cooling air inside insert and outlet orifice to remove cooling air portion from blade. The insert defines annular cavity arranged between outer side wall thereof and inner blade wall. Blade has bridges located in cavity part between the insert and inner surface of rear edge to increase blade rigidity. One insert end is fixed to blade. Another one is installed so that the insert end may slide along inner edge of blade under the action of mutual thermal insert expansion relatively inner blade wall. Orifices are created in opened insert so that the orifices are located only in two insert areas. Orifices of the first group are opposite to inner surface of front edge. Orifices of the second group are opposite to inner surface of rear edge to prevent air jet impingement upon bridges.

EFFECT: increased cooling ability.

5 cl, 6 dwg