Turbine blades have internal passages that provide cooling during operation in a hightemperature engine. The design of the cooling passages is critical to achieve near uniformtemperature of the blade during operation. The temperature of the blade is dependent on the thermal properties of the blade ...
A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine blade. The first passage may be configured to provide ...
Cooling holes are generally dispersed throughout the blade and connect the internal cooling passages with the outer surface of the blade. The steady stream of exiting air creates a film on the blade surface that additionally protects it from exposure to the hot gas. The cooling effectiveness and...
External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form a protective layer between the blade surface and hot gas-path flow. For internal cooling, this presentation focuses on ...
A typical advanced gas turbine’s first-stage blade cooling scheme is shown in Fig. 2.20, providing solution choices for different cooling needs. Three methods are featured including convection, film, and impingement. In addition, advanced features including serpentine passages and turbulence promoters ...
In addition, there are some studies [12], [13], [14], [15], [16] in which blade simulated by conjugate (or coupled) heat transfer method using one-dimensional (1-D) simulation for internal cooling passages. Short calculation time is the most important reason that in these works, 1-D...
A turbine blade for use in an industrial gas turbine engine, the blade having a squealer pocket with a plurality of discrete curved cooling channels to cool the blade tip and to red
A turbine blade includes a plurality of cooling passages each having a turbulated section of the passage preferentially located along the portion of the turbine blade subjected to the highest temperat
Due to the contraction of the insert (<B>6</B>) after a certain temperature threshold value is exceeded, the cooling system (<B>12</B>) of the turbine blade (<B>1</B>) is enlarged in the interior. The size of the cooling system (<B>12</B>) (effectiveness of the cooling, ...
3. A turbine blade according to claim 1 wherein the channels are adapted for coolant flow therethrough, said channels communicate with the central void of the blade and cooling passages are provided to conduct the coolant from the void to holes in the external surface of the blade. ...