Gas turbine airfoil with a cooling air regulating seal

Claim 2

A gas turbine comprising: a) a compressor for producing compressed air; b) a combustor for heating at least a portion of said compressed air, thereby producing a hot compressed gas; and c) a turbine for expanding said hot compressed gas so as to produce shaft power, said turbine having an airfoil disposed therein that is exposed to said hot compressed gas, said airfoil having: (i) a plurality of walls defining a cavity enclosed thereby, (ii) a member disposed inside said cavity and enclosing a portion thereof, a first cooling fluid passage formed between said member and said walls, (iii) a second cooling fluid passage extending from said cavity and in flow communication with said first cooling fluid passage, (iv) a seal for regulating the flow of cooling fluid between said first and second cooling passages, said seal comprising a flexible leg portion; and (v) means for causing said flexible leg portion to be pressed against one of said walls in response to a pressure differential between cooling fluid flowing through said first and second passages.

Claim 3

The gas turbine according to claim 1, wherein at least a portion of said seal extends between at least one of said walls and said member.

Claim 4

The gas turbine according to claim 1, wherein said means for pressing said flexible leg portion against said one of said walls comprises a projection extending outwardly from said one of said walls.

Claim 5

The gas turbine according to claim 1, wherein said seal has a plurality of holes formed therein.

Claim 6

The gas turbine according to claim 1, wherein said member is substantially tubular and has a plurality of cooling fluid holes formed therein, said cooling fluid holes in flow communication with said first cooling fluid passage.

Claim 7

The gas turbine according to claim 1, wherein said second cooling fluid passage is in flow communication with said hot compressed gas being expanded in said turbine.

Claim 8

The gas turbine according to claim 6, wherein said airfoil has a trailing edge portion, said second cooling fluid passage being formed in said trailing edge portion.

Claim 9

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.

Claim 10

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.

Claim 11

The air foil according to claim 8, wherein said first and second walls are exposed to said hot compressed gas.

Claim 12

The air foil according to claim 8 wherein said first wall has a surface exposed to said hot compressed gas, a cooling fluid passage being formed in said first wall, said cooling fluid passage having means for directing cooling fluid from said cavity to flow over said first wall surface.

Claim 13

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.

Claim 14

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.

Claim 15

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.

Claim 16

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.

Claim 17

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.

Claim 18

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.