Gas turbine airfoil with a cooling air regulating seal

In a gas turbine having a turbine section through which a hot compressed gas flows and to which a cooling fluid is supplied, an airfoil comprising:

• a) first and second walls defining a cavity therebetween;
• b) an insert disposed in said cavity and having means for distributing at least a portion of said cooling fluid around said cavity, said insert having a trailing edge portion;
• and
• c) sealing means projecting from the trailing edge portion of said insert and extending to said first and second walls, said sealing means having a plurality of cooling fluid holes formed therein.

In a gas turbine having a turbine section through which a hot compressed gas flows and to which a cooling fluid is supplied, an airfoil comprising:

• a) at least first and second walls defining a cavity therebetween, at least one of said first and second walls forming a trailing edge portion of said airfoil, said first wall being exposed to said flow of hot compressed gas;
• b) an insert disposed in said cavity and forming first and second cooling fluid passages disposed between said insert and said first and second walls, respectively, said first and second cooling fluid passages being in flow communication;
• c) a third cooling fluid passage formed in said trailing edge portion and being in flow communication with said hot compressed gas and with said first and second cooling fluid passages;
• d) a fourth cooling fluid passage formed in said first wall and placing said first cooling fluid passage in flow communication with said hot compressed gas;
• and
• e) a seal for restricting cooling fluid flow from said first and second cooling fluid passages to said third cooling fluid passage so as to increase the difference in pressure between said cooling fluid flowing in said first passage and said hot compressed gas, thereby facilitating cooling fluid flow from said first cooling fluid passage to said hot compressed gas through said fourth cooling fluid passage, said seal having a first portion disposed between said first cooling fluid passage and said third cooling fluid passage and a second portion disposed between said second cooling fluid passage and said third cooling fluid passage, said first and second portions of said seal having a plurality of cooling fluid holes formed therein.

In a gas turbine having a turbine section through which a hot compressed gas flows and to which a cooling fluid is supplied, an airfoil comprising:

• a) at least first and second walls defining a cavity therebetween, at least one of said first and second walls forming a trailing edge portion of said airfoil, said first wall being exposed to said flow of hot compressed gas;
• b) an insert disposed in said cavity and forming first and second cooling fluid passages disposed between said insert and said first and second walls, respectively, said first and second cooling fluid passages being in flow communication;
• c) a third cooling fluid passage formed in said trailing edge portion and being in flow communication with said hot compressed gas and with said first and second cooling fluid passages;
• d) a fourth cooling fluid passage formed in said first wall and placing said first cooling fluid passage in flow communication with said hot compressed gas;
• and
• e) a seal for restricting cooling fluid flow from said first and second cooling fluid passages to said third cooling fluid passage so as to increase the difference in pressure between said cooling fluid flowing in said first passage and said hot compressed gas, thereby facilitating cooling fluid flow from said first cooling fluid passage to said hot compressed gas through said fourth cooling fluid passage, said seal having a first flexible portion disposed between said first cooling fluid passage and said third cooling fluid passage, and a second flexible portion disposed between said second cooling fluid passage and said third cooling fluid passage.

In a gas turbine having a turbine section through which a hot compressed gas flows and to which a cooling fluid is supplied, an airfoil comprising:

• a) at least first and second walls defining a cavity therebetween, at least one of said first and second walls forming a trailing edge portion of said airfoil, said first wall being exposed to said flow of hot compressed gas;
• b) an insert disposed in said cavity and forming first and second cooling fluid passages disposed between said insert and said first and second walls, respectively, said first and second cooling fluid passages being in flow communication;
• c) a third cooling fluid passage formed in said trailing edge portion and being in flow communication with said hot compressed gas and with said first and second cooling fluid passages;
• d) a fourth cooling fluid passage formed in said first wall and placing said first cooling fluid passage in flow communication with said hot compressed gas;
• and
• e) means for restricting cooling fluid flow from said first and second cooling fluid passages to said third cooling fluid passage so as to increase the difference in pressure between said cooling fluid flowing in said first passage and said hot compressed gas, thereby facilitating cooling fluid flow from said first cooling fluid passage to said hot compressed gas through said fourth cooling fluid passage, said cooling fluid restricting means comprising:
• (i) a seal having a first portion disposed between said first cooling fluid passage and said third cooling fluid passage and a second portion disposed between said second cooling fluid passage and said third cooling fluid passage,
• (ii) means for causing said first and second portions of said seal to be pressed against said first and second walls.