Turbine airfoil with arrangement of multi-outlet film cooling holes

Abstract: A turbine airfoil incorporates a film cooling arrangement composed of a plurality of multi-outlet holes defined through the opposite side walls to permit flow of cooling air from the hollow interior chamber of the airfoil to the external surface of the side walls. Each multi-outlet hole includes a flow inlet (52) at the internal surface of the side walls and communicating with the hollow interior chamber, at least a pair of flow outlets (58A,B) at the exterior surface of the side walls, and at least a pair of flow branches (64A,B) extending through the side walls and between the flow inlet and the flow outlets. The flow branches merge and intersect with one another at the flow inlet. The flow outlets are displaced preferably downstream of the flow inlet relative to the direction of gas flow past the external surface of the side walls of the airfoil. The flow branches extend through the side walls in inclined relation to the external surface of the side walls.

Description: Field of the Invention The present invention relates generally to gas turbine engine and, more particularly, to a turbine airfoil having an arrangement of multi-outlet film cooling holes according to the preamble of Claim 1 and as disclosed in GB-A-22 02 907. Description of the Prior Art Gas turbine engines conventionally comprise an axial flow compressor which compresses air to the proper pressure required for supporting combustion of fuel in a combustion chamber. The combustion gases then pass to a turbine which powers the axial flow compressor. After passing through the turbine, the high energy combustion gas flow may be employed to drive a power turbine which is connected to an output shaft on which may be mounted a propeller, fan or other device. Alternatively, the high energy combustion gas flow may be utilized directly as a thrust to provide motive power, as in turbojet engines commonly used for aircraft. It is well known that efficiency of turbine engines increases with increase in temperature of the combustion gas flow. A limiting factor in the gas flow temperature is the high temperature capability of the various turbine, stator and rotor airfoils. As used herein, reference to a turbine airfoil includes both rotor blades and stator vanes. Various approaches to internally cooling the airfoils have been proposed to increase the upper operating temperature capability of the engines. One advantageous approach is "film cooling" of the airfoils. The term "film cooling" refers to the technique of cooling the external surface of the airfoil by injecting a relatively cooled air along the external surface which moves sufficiently slowly so that the layer acts as an insulative layer to reduce unwanted heating of the external surface of the airfoil by the adjacent hot gas flow stream. It is conventional to provide film cooling holes through the wall of the airfoil to exhaust pressurized cooling air flow from the interior chamber of the airfoil through the airfoil wall to the exterior surface of the airfoil. Examples of different arrangements and configurations of film cooling holes that have been proposed in the prior art are disclosed in U. S. patents to Howald (3,527,543) Corrigan (4,221,539) and Durgin et al (4,297,077). In one proposal (GB-A-2202907) further cooling means for the leading edge of an airfoil are provided by the provision of vortex chambers between the interior of the airfoil and the outer surface but having otherwise standard film forming outlet holes. Although the hole configurations of the cited patents are steps in the right direction for providing film cooling of airfoils in order to increase the operating temperature and thereby the efficiency of the turbine engines, a need for additional improvement still remains. SUMMARY OF THE INVENTION The present invention provides an arrangement of multi-outlet film cooling holes in a turbine airfoil designed to satisfy the aforementioned need. The advantages of the multi-outlet holes are higher film cooling effectiveness, larger convection cooling area inside the film holes, improved film coverage. The arrangement of multi-outlet holes are suitable for use in both large and small airfoils and can be fabricated by a laser drilling process. According to a first aspect of the present invention there is provided in a turbine airfoil having leading and trailing edges and opposite side walls defining pressure and suction sides and merging together at said leading and trailing edges to define a hollow interior chamber for communication of cooling air flow to said side walls of said airfoil, said side walls extending generally in the direction of gas flow past said airfoil from said leading edge to said trailing edge of said airfoil a film cooling arrangement comprising (a) a portion of at least one of said side walls, said side wall portion having an external surface extending in the direction of gas flow past said airfoil and an internal surface spaced from said external surface and communicating with said hollow interior chamber; and, characterized by, (b) means defining a plurality of multi-outlet holes through said side wall portion to permit flow of cooling air from said hollow interior chamber to said external surface of said side wall; and (c) each multi-outlet hole including a flow inlet defined at said internal surface and communicating with said hollow interior chamber, at least a pair of flow outlets defined at said exterior surface, and at least a pair of flow branches extending through the side wall portion between said flow inlet and said flow outlets, said flow branches merging and intersecting with one another at said flow inlet. According to a second aspect of the invention, there is provided in a turbine airfoil having leading and trailing edges and opposite side walls defining pressure and suction sides and merging together at said leading and trailing edges to define a hollow interior chamber for communication of cooling air flow to said side walls of said airfoil, said side walls extending generally in the direction of gas flow past said airfoil from said leading edge to said trailing edge of said airfoil, a film cooling arrangement comprising (a) a portion of at least one of said side walls, said side wall portion having an external surface extending in the direction of gas flow past said airfoil and an internal surface spaced from said external surface and communicating with said hollow interior chamber; and, characterized by, (b) means defining a plurality of multi-outlet holes through said side wall portion to permit flow of cooling air from said hollow interior chamber to said external surface of said side wall; (c) each multi-outlet hole including a flow-inlet defined at said internal surface and communicating with said hollow interior chamber, at least a pair of flow outlets defined at said exterior surface, and at least a pair of flow branches extending through the side wall portion between said flow inlet and said flow outlets, said flow branches merging and intersecting with one another at said flow inlet; (d) said flow outlets of each said hole being displaced downstream of said flow inlet relative to the direction of gas flow past said external surface of said side wall portion of said airfoil; and (e) said flow branches of each said hole extending through said side wall portion in inclined relation relative to said external surface of said side wall portion of said airfoil and the direction of gas flow past said external surface of said airfoil side wall portion. The flow outlets of each hole are preferably displaced downstream of the flow inlet relative to the direction of gas flow past the external surface of the side wall portion. The flow branches of each hole may extend through the side wall portion in inclined relation relative to the external surface of the side wall portion and the direction of gas flow past the external surface of the side wall portion. Different embodiments of the multi-outlet holes are provided. In a first embodiment, the flow branches and flow outlets of each hole are disposed in a plane extending in generally parallel relation to the direction of gas flow past the external surface of the side wall portion. Further, one of the flow branches is shorter in axial length than the other. Also, corresponding ones of the flow outlets of the respective holes are aligned with one another in respective rows extending in generally transverse relation to the direction of gas flow past the external surface of the side wall portion. In a second embodiment, one of the flow branches of each hole is a primary flow branch and the other of the flow branches is a pair of secondary flow branches. In the preferred embodiment, the primary flow branch has a cross-sectional size that is larger than that of each of the secondary flow branches. Further, the flow outlet of the primary flow branch is displaced downstream of the flow outlets of the secondary flow branches relative to the direction of gas flow past the external surface of the side wall portion. Also, the secondary flow branches are aligned with one another in a plane extending in inclined relation relative to the external surface of the side wall portion and the direction of gas flow past the external surface of the side wall portion. In a third embodiment, the flow outlets of each hole are aligned in a row extending in generally transverse relation to the direction of gas flow past the external surface of the side wall portion. Further, the flow outlets of the respective holes are aligned with one another in a common row extending in generally transverse relation to the direction of gas flow past the external surface of the side wall portion. Also, the flow branches are substantially equal to one another in axial length and are aligned with one another in a plane extending in inclined relation relative to the external surface of the side wall portion and the direction of gas flow past the external surface of the side wall portion. These and other features and advantages and attainments of the present invention will become apparent to those skilled in the art upon a reading of the following detailed description when taken in conjunction with the drawings wherein there is shown and described an illustrative embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS In the course of the following detailed description, reference will be made to the attached drawings in which: Fig. 1 is a perspective view of a prior art turbine engine blade having holes in the blade airfoil for exit of cooling air therefrom. Fig. 2 is an enlarged cross-sectional view of the prior art blade airfoil taken along line 2--2 of Fig. 1. Fig. 3 is an enlarged elevational view of a fragmentary portion of the prior art blade enclosed by dashed oval 3--3 of Fig. 1. Fig. 4 is a cross-sectional view taken along line 4--4 of Fig. 3. Fig. 5 is a view similar to that of Fig. 3 but illustrating a first embodiment of the multi-outlet film cooling holes of the present invention. Fig. 6 is a cross-sectional view taken along line 6--6 of Fig. 5. Fig. 7 is a view similar to that of Fig. 5 but illustrating a second embodiment of the multi-outlet film cooling holes of the present invention. Fig. 8 is a cross-sectional view taken along line 8--8 of Fig. 7. Fig. 9 is a view similar to that of Fig. 7 but illustrating a third embodiment of the multi-outlet film cooling holes of the present invention. Fig. 10 is a cross-sectional view taken along line 10--10 of Fig. 9. DETAILED DESCRIPTION OF THE INVENTION In the following description, like reference characters designate like or corresponding parts throughout the several views. Also in the following description, it is to be understood that such terms as "forward", "rearward", "left", "right", "upwardly", "downwardly", and the like, are words of convenience and are not to be construed as limiting terms. Prior Art Turbine Engine Blade Referring now to the drawings, and particularly to Figs. 1 and 2, there is illustrated a prior art gas turbine engine hollow blade, generally designated 10. The hollow blade 10 includes an airfoil 12 having pressure and suction sides 14, 16 and leading and trailing edges 18, 20, and a base 22 mounting the airfoil 12 to a rotor (not shown) of the engine (not shown). The base 22 has a platform 24 rigidly mounting the airfoil 12 and a dovetail root 26 for attaching the blade 10 to the rotor. The airfoil 12 has opposite side walls 28, 30 defining the pressure and suction sides 14, 16 of the airfoil 12 which merge together at the leading and trailing edges 18, 20 of the airfoil 12 and are rigidly attached upright on the platform 24. The airfoil 12 also has an end cap 32 which closes the outer ends of the side walls 28, 30. The side walls 28, 30, leading and trailing edges 18, 20, and end cap 32 of the airfoil 12 contain small apertures or holes 34 which permit passage and exit of cooling air from the interior to the exterior of the blade airfoil 12. Cooling air flows into and upwardly through the base 22 of the blade 10 to the airfoil 12. The airfoil 12 includes a plurality of interior spaced ribs or transverse walls 36 which extend across the hollow interior of the airfoil 12 and rigidly interconnected with the opposite side walls 28, 30 so as to define a series of interior cavities 38 in the airfoil 12 in a hollow interior chamber 40 of the airfoil. As an example, the ribs 36 can extend vertically and alternately connect to and terminate short of the end cap 32 at their upper ends and of the platform 24 of the base 22. In such fashion, the ribs 36 define serpentine arrangements (not shown) of cavities and passages within the interior of the airfoil 12 causing cooling air to flow along internal serpentine paths and exit through the holes 34 in the side walls 28, 30, leading and trailing edges 18, 20, and end cap 32 of the airfoil 12. As seen in Figs. 3 and 4, the cooling holes 34 typically are circular in cross-section. The cooling holes 34 extending through the side walls 28, 30 are axially aligned substantially normal to the internal and external surfaces 42, 44 of the blade side walls 28, 30 and thus to the direction of hot gas flow, being represented by arrow H, passing the external surface 44 of the side walls. In previously cited U. S. Patent 3,527,543 to Howald, assigned to the same assignee as the present invention, cooling holes are shown that are inclined in a direction toward the downstream flow of the hot gas. In the case of both hole configurations, the objective is to achieve film cooling of the external surface 44 of the airfoil 12 by entraining the cooling air exiting the holes 34 within a boundary layer L of low velocity gas that exists between the hot combustion gases, represented by the arrow H which are traveling at high velocity past the airfoil 12, and the airfoil external surface 44 itself. Airfoil With Multi-Outlet Film Cooling Holes of the Present Invention Referring to Figs. 5-10, there is illustrated different embodiments of multi-outlet holes 46, 48, 50 in accordance with the present invention. Any of the illustrated arrangements of multi-outlet holes 46, 48, 50 can be substituted in place of the prior art holes 34 in the side walls 28, 30 of the blade airfoil 12. These multi-outlet holes 46, 48, 50 have configurations which more effectively entrain the cooling air exiting the holes in the boundary layer L of low velocity gas flow and thereby more effectively provide the desired film cooling of the airfoil external surface 44 by avoiding dissipation of the cooling air into the high velocity hot combustion gas flow H. Referring to Figs. 5-10, each multi-outlet hole 46, 48, 50 includes a flow inlet 52, 54, 56 defined at the internal surface 42 and communicating with the hollow interior chamber 40, at least a pair of flow outlets 58, 60, 62 defined at the exterior surface 44, and at least a pair of flow branches 64, 66, 68 extending through the side walls 28, 30 between the flow inlet 52, 54, 56 and the flow outlets 58, 60, 62. The flow branches 64, 66, 68 merge and intersect with one another at the flow inlet 52, 54, 56. The flow inlet 52, 54, 56, flow outlets 58, 60, 62 and flow branches 64, 66, 68 preferably have circular cross-sectional configurations. The flow branches 64, 66, 68 are substantially straight, of uniform cross-sectional size, and overall define right cylinders. The flow outlets 58, 60, 62 are displaced preferably downstream of the flow inlet 52, 54, 56 relative to the direction of gas flow H past the external surface 44 of the side walls 28, 30 of the airfoil 12. The flow branches 64, 66, 68 extend through the side walls 28, 30 in inclined relation to the internal and external surfaces 42, 44 of the side walls 28, 30 of the airfoil 12 and to the direction of gas flow H past the external surface 44 of the side walls 28, 30. Referring to the first embodiment of Figs. 5 and 6, the pairs of flow branches 64 and flow outlets 58 of each multi-outlet hole 46 are disposed in a plane extending in generally parallel relation to the direction of gas flow H past the external surface 44 of the airfoil side walls 28, 30. Further, one of the flow branches 64A is preferably longer in axial length than the other flow branch 64B. The flow outlet 58A of the longer flow branch 64A is displaced preferably downstream of the flow outlet 58B of the shorter flow branch 64B relative to the direction of gas flow H past the external surface 44 of the airfoil side walls 28, 30. Also, corresponding ones of the flow outlets 58 of the respective holes 46 are aligned with one another in respective rows extending in generally transverse relation to the direction of gas flow H past the external surface 44 of the airfoil side walls 28, 30. Further, corresponding ones of the flow branches 64A, 64B are aligned with one another in planes extending in different inclined relations relative to the internal and external surfaces 42, 44 of the side walls 28, 30 and the direction of gas flow H past the external surface 44 of the airfoil side walls. The plane of the shorter flow branches 64B is at a steeper incline than the plane of the longer flow branches 64A. Referring to the second embodiment of Figs. 7 and 8, flow branch 66A, which in the preferred embodiment is the longest one of the flow branches 66 of each multi-outlet hole 48, is a primary flow ranch 66A and the other flow branch 66B is split into a pair of secondary flow branches 66B together having a V-shaped configuration. The primary flow branch 66A and outlet 60A have a cross-sectional size that is preferably larger than that of each of the secondary flow branches 66B and outlets 60B. Further, the flow outlet 60A of the primary flow branch 66A is displaced preferably downstream of the flow outlets 60B of the secondary flow branches 66B relative to the direction of gas flow H past the external surface 44 of the airfoil side walls 28, 30. Also, the secondary flow branches 66B are aligned with one another in a plane extending in inclined relation relative to the internal and external surfaces 42, 44 of the side walls 28, 30 and the direction of gas flow H past the external surface 44 of the airfoil side walls. The plane of the secondary flow branches 66B is at a steeper incline than the plane defined by the primary flow branches 66A. Referring to the third embodiment of Figs. 9 and 10, the flow outlets 62 of each multi-outlet hole 50 are preferably aligned with one another in a common row extending in generally transverse relation to the direction of gas flow H past the external surface 44 of the airfoil side walls 28, 30. Further, the flow branches 68 are preferably substantially equal to one another in axial length, and together have a V-shaped configuration. Also, the flow branches 68 are aligned with one another in a plane extending in inclined relation relative to the internal and external surfaces 42, 44 of the side walls 28, 30 and the direction of gas flow H past the external surface 44 of the airfoil side walls. The advantages of the configurations of the multi-outlet holes 46, 48, 50 are higher film cooling effectiveness, larger convection cooling area inside the film holes, improved film coverage. The arrangement of multi-outlet holes 46, 48, 50 are suitable for use in both large and small airfoils and can be fabricated by a laser drilling process. It is thought that the present invention and many of its attendant advantages will be understood from the foregoing description and it will be apparent that various changes may be made in the form, construction and arrangement of the parts thereof without departing from the scope of the invention as defined in the claims, the forms hereinbefore described being merely preferred or exemplary embodiments thereof.

Claims: A turbine airfoil (10) having leading and trailing edges (18,20) and opposite side walls (28,30) defining pressure and suction sides (28,30) and merging together at said leading and trailing edges (18,20) to define a hollow interior chamber (38) for communication of cooling air flow to said side walls (28,30) of said airfoil, said side walls extending generally in the direction of gas flow past said airfoil from said leading edge (18) to said trailing edge (20) of said airfoil, a film cooling arrangement comprising- (a) a portion of at least one of said side walls (28,30), said side wall portion having an external surface (44) extending in the direction of gas flow past said airfoil (10) and an internal surface (42) spaced from said extemal surface (44) and communicating with said hollow interior chamber, (38) and, CHARACTERIZED BY: (b) means defining a plurality of multi-outlet holes (46,48,50) through said side wall portion to permit flow of cooling air from said hollow interior chamber to said extemal surface of said side wall; and (c) each multi-outlet hole including a flow inlet (52, 54, 56) defined at said internal surface (42) and communicating with said hollow interior chamber, at least a pair of flow outlets (58, 60, 62) defined at said exterior surface, and at least a pair of flow branches (64,66,68) extending through the side wall portion between said flow inlet (52,54,56) and said flow outlets (58,60,62) said flow branches (64,66,68) merging and intersecting with one another at said flow inlet (52,54,56). The turbine airfoil as recited in claim 1, CHARACTERIZED BY said flow outlets (58,60,62) of each said hole (46,48,50) being displaced downstream of said flow inlet (52,54,56) relative to the direction of gas flow past said external surface (44) of said side wall portion. The turbine airfoil as recited in Claim 2, CHARACTERIZED BY said flow branches (64,66,68) of each said hole (46,48,50) extending through said side wall portion in inclined relation relative to said external surface (44) of said side wall portion and the direction of gas flow past said external surface (44) of said side wall portion. The turbine airfoil as recited in Claim 2, CHARACTERIZED BY said flow branches (64) of each said hole (46) being disposed in a plane extending in generally parallel relation to the direction of gas flow past said extemal surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 4, CHARACTERIZED BY one of said flow branches (648) of each said hole (46) being shorter in axial length than the other of said flow branches (64A). The turbine airfoil as recited in claim 1, CHARACTERIZED BY said flow outlets (58A,58B) of each said hole (46) being aligned in a row extending in generally parallel relation to the direction of gas flow past said extemal surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 1, CHARACTERIZED BY corresponding ones of said flow outlets (60A,60B) of said respective holes (48) being aligned with one another in respective rows extending in generally transverse relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil The turbine airfoil as recited in claim 1, CHARACTERIZED BY said flow outlets (62) of each said hole (50) being aligned in a row extending in generally transverse relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in claim 1, CHARACTERIZED BY said flow outlets (62) of said respective holes (50) being aligned with one another in a common row extending in generally transverse relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 9, CHARACTERIZED BY said flow branches (68) of each said hole (50) being aligned with one another in a plane extending in inclined relation relative to said external surface (44) of said side wall portion and the direction of gas flow past said extemal surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 10, CHARACTERIZED BY said flow branches (68) of each said hole (50) being substantially equal to one another in axial length. The turbine airfoil as recited in Claim 1, CHARACTERIZED BY one (66A) of said flow branches of each said hole (50) being a primary flow branch and the other (66B) of said flow branches being a pair of secondary flow branches. The turbine airfoil as recited in Claim 12, CHARACTERIZED BY said primary flow branch (66A) has a cross-sectional size that is larger than that of each of said secondary flow branches (66B). The turbine airfoil as recited in Claim 12, CHARACTERIZED BY said flow outlet of said primary flow branch (66A) is displaced downstream of said flow outlets of said secondary flow branches (66B) relative to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 12, CHARACTERIZED BY said secondary flow branches (66B) are aligned with one another in a plane extending in inclined relation relative to said external surface of said side wall portion and the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. A turbine airfoil (10) having leading and trailing edges (18,20) and opposite side walls defining pressure and suction sides (28,30) and merging together at said leading and trailing edges to define a hollow interior chamber (38) for communication of cooling air flow to said side walls of said airfoil, said side walls extending generally in the direction of gas flow past said airfoil from said leading edge to said trailing edge of said airfoil, a film cooling arrangement comprising- (a) a portion of at least one of said side walls, said side wall portion having an external surface (44) extending in the direction of gas flow past said airfoil and an internal surface (42) spaced from said external surface and communicating with said hollow interior chamber; and, CHARACTERIZED BY: (b) means defining a plurality of multi-outlet holes (46,48,50) through said side wall portion to permit flow of cooling airfrom said hollow interior chamber to said external surface of said side wall; and (c) each multi-outlet hole including a flow-inlet (52, 54, 56) defined at said internal surface (42) and communicating with said hollow interior chamber, at least a pair of flow outlets (58, 60, 62) defined at said exterior surface, and at least a pair of flow branches (64,66,68) extending through the side wall portion between said flow inlet and said flow outlets, said flow branches merging and intersecting with one another at said flow inlet; (d) said flow outlets (58,60,62) of each said hole (46,48,50) being displaced downstream of said flow inlet (52,54,56) relative to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil; (e) said flow branches (64,66,68) of each said hole (46,48,50) extending through said side wall portion in inclined relation relative to said external surface (44) of said side wall portion of said airfoil and the direction of gas flow past said external surface (44) of said airfoil side wall portion. The turbine airfoil as recited in Claim 16, CHARACTERIZED BY said flow branches (64) of each said hole (46) being disposed in a plane extending in generally parallel relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 17, CHARACTERIZED BY one of said flow branches (64B) of each said hole (46) being shorter in axial length than the other of said flow branches (64A). The turbine airfoil as recited in claim 1, CHARACTERIZED BY said flow outlets (58A,58B) of each said hole (46) being aligned in a row extending in generally parallel relation to the direction of gas flow past said extemal surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 16, CHARACTERIZED BY corresponding ones of said flow outlets (60A,60B) of said respective holes (48) being aligned with one another in respective rows extending in generally transverse relation to-the direction of gas flow past said external surface (44) of said side wall portion of said airfoil The turbine airfoil as recited in claim 16, CHARACTERIZED BY said flow outlets (62) of each said holes (50) being aligned in a row extending in generally transverse relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in claim 16, CHARACTERIZED BY said flow outlets (62) of said respective holes (50) being aligned with one another in a common row extending in generally transverse relation to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 22, CHARACTERIZED BY said flow branches (68) of each said holes (50) being aligned with one another in a plane extending in inclined relation relative to said external surface (44) of said side wall portion and the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 23, CHARACTERIZED BY said flow branches (68) of each said hole (50) being substantially equal to one another in axial length. The turbine airfoil as recited in Claim 16, CHARACTERIZED BY one (66A) of said flow branches of each said hole (50) being a primary flow branch and the other (66B) of said flow branches being a pair of secondary flow branches. The turbine airfoil as recited in Claim 25, CHARACTERIZED BY said primary flow branch (66A) has a cross-sectional size that is larger than that of each of said secondary flow branches (66B). The turbine airfoil as recited in Claim 25, CHARACTERIZED BY said flow outlet of said primary flow branch (66A) is displaced downstream of said flow outlets of said secondary flow branches (66B) relative to the direction of gas flow past said external surface (44) of said side wall portion of said airfoil. The turbine airfoil as recited in Claim 25, CHARACTERIZED BY said secondary flow branches (66B) are aligned with one another in a plane extending in inclined relation relative to said external surface of said side wall portion and the direction of gas flow past said external surface (44) of said side wall portion of said airfoil.

Inventors: LEE CHING-PANG, LEE, CHING-PANG
Applicants: GEN ELECTRIC, GENERAL ELECTRIC COMPANY
Application year: 1992
Main classification: F01D5
IPC codes: F01D9, F01D5, F02C7