TH14718B - Rotor blades of gas turbines - Google Patents

Abstract

The DC60 (18/10/45) provided is the rotor blades of the gas turbine generator. Which contains many first class cooling holes for refrigerant gas flow Which bore part of the impeller along its length and many second type cooling holes. For refrigerant gas flow pierced in the cover Along its horizontal direction In order to make contact with the first type of cooling holes And was created In such a way that the refrigerant gas can flow in a uniform distribution Many of Class I cooling holes (3) holes for refrigerant gas flow are drilled in the impeller (2), and numerous type II cooling holes (5) for refrigerant gas flow. Is pierced in the cover (1) all the way in its horizontal direction Type II (5) cooling holes contact type I (3) cooling holes, double through hole (4) and second (5) type cooling holes are drilled alternately on the side. after And the belly of the propeller is the propeller of the gas turbine. Which contains many first class cooling holes for refrigerant gas flow Which bore part of the impeller along its length and many second type cooling holes. For refrigerant gas flow pierced in the cover Along its horizontal direction In order to make contact with the first type of cooling holes And was created In such a way that the refrigerant gas can flow in a uniform distribution Many of Class I cooling holes (3) holes for refrigerant gas flow are drilled in the impeller (2), and numerous type II cooling holes (5) for refrigerant gas flow. Is pierced in the cover (1) all the way in its horizontal direction Type II (5) cooling holes are in contact with type I (3) cooling holes, double through hole (4) and second (5) type cooling holes are drilled in a bolt on the top. after And the belly of the rotor blades

Claims (6)

Clause (all) that will not appear on the advertisement page: clause 1. The propeller of a gas turbine propeller consists of: - longitudinal, rear and ventral blades - a cover at one end of the propeller section. As for the cover With its horizontal direction with the back and abdomen Aligned with the back and abdomen Of the impeller section, respectively - many first type cooling holes For the flow of refrigerant gas is penetrated in the said impeller section. In the direction of its length And cooling holes Second, the bulk flow of the refrigerant gas is penetrated in the hood all the way. In its horizontal direction, such second type of cooling holes are characteristically consecutive fluid with holes. Corresponding cooling of many first type cooling holes with one relationship. Aim for one hole Which many of the second type of cooling holes Switch position on the side The back and the abdomen of the aforementioned cover. 2. Rotator of the gas turbine of claim 1, where the cooling hole Second class a lot Contact with many first cooling holes. Through the third type of hole Many are pierced in such a cover. In the direction of the length of the blade Each hole of the aforementioned third class consists of two steps, including the upper part covered by a joint. 3. Rotator of the gas turbine of claim 1, which is the cooling hole. The second class is parallel to each other. 4. Rotator of the gas turbine of claim 1, which the cover is Have an outer surface The inner surface and the side surface between the outer surface And the inner surface, many second type cooling holes open on the side surface. 5. Rotator of the gas turbine of claim 1, where the cooling holes First class And many second type cooling holes Together Each cooling way, respectively Which extends from the impeller section and through the said cover And there is no contact between each other according to its scope. 6. Rotators of the gas turbine of claim 1, which relates to One hole per such hole Is set so that many first type cooling holes Stay in contact with fluid with one And only one hole of many second type cooling holes