Gas turbine engine airfoil trailing edge passage and core for making same

Abstract

An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.

Claims

1. An airfoil comprising: a body including leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface, a cooling passage extending in a radial direction from a root to a tip, and a trailing edge cooling passage interconnecting the cooling passage to the trailing edge, the trailing edge cooling passage including radial columns comprising first and second pedestals of different diameters and arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different diameters, wherein one of the first and second pedestals is nearer to the trailing edge than the other of the first and second pedestals, the one of the first and second pedestals are larger than the other of the first and second pedestals, wherein the second pedestals are arranged in columns spaced apart from one another in a chord-wise direction, and a center of the columns are spaced 2.5 diameters of the second pedestals from one another, and including third pedestals that are of a different diameter than the first and second pedestals.

2. The airfoil according to claim 1, wherein the first pedestals have a diameter twice that of the diameter of the second pedestals.

3. The airfoil according to claim 1, wherein one of the columns of second pedestals is spaced 1.5 diameters of the first pedestals from a column of first pedestals.

4. The airfoil according to claim 1, wherein the third pedestals have a diameter that is two-thirds of the diameter of the first pedestal.

5. The airfoil according to claim 1, wherein the first pedestal has a diameter that is 0.030 inch (0.76 mm).

6. The airfoil according to claim 1, comprising a trailing edge core portion providing first and second holes corresponding to the first and second pedestals, the trailing edge core portion constructed from a refractory metal.

7. The airfoil according to claim 1, wherein the trailing edge cooling passage has a corner region without pedestals.

8. The airfoil according to claim 7, wherein the corner region without pedestals is within a radius of 0.075 in (1.91 mm).

9. The airfoil according to claim 8, wherein the corner region is defined by a second radius of 0.050 inch (1.27 mm).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

(2) FIG. 1 is a schematic view of an example gas turbine engine incorporating the disclosed airfoil.

(3) FIG. 2A is a perspective view of the airfoil having the disclosed cooling passage.

(4) FIG. 2B is an end view of the airfoil illustrating directional references.

(5) FIG. 3A is a perspective view of an example core providing a core tie corresponding to a dirt purge passage, with an exterior airfoil surface shown in phantom.

(6) FIG. 3B is a partial cross-sectional view of the core shown in a wax mold.

(7) FIG. 3C is a cross-sectional view of a second core portion and trailing edge core portion for producing a trailing edge cooling passage.

(8) FIG. 3D is an enlarged view of a first end portion of the second core portion and trailing edge core portion.

(9) FIG. 4A is a cross-sectional view through the airfoil taken along line 4A-4A in FIG. 2A.

(10) FIG. 4B is an enlarged view of a portion of the airfoil illustrated in FIG. 4A.

(11) FIG. 5 is an enlarged view of the second end portion of the core illustrated in FIG. 3A with the corresponding airfoil cooling passages shown in phantom.

(12) FIG. 6 is an enlarged view of a portion of the trailing edge core portion.

DETAILED DESCRIPTION

(13) FIG. 1 schematically illustrates a gas turbine engine 10 that includes a fan 14, a compressor section 16, a combustion section 18 and a turbine section 11, which are disposed about a central axis 12. As known in the art, air compressed in the compressor section 16 is mixed with fuel that is burned in combustion section 18 and expanded in the turbine section 11. The turbine section 11 includes, for example, rotors 13 and 15 that, in response to expansion of the burned fuel, rotate, which drives the compressor section 16 and fan 14.

(14) The turbine section 11 includes alternating rows of blades 20 and static airfoils or vanes 19. It should be understood that FIG. 1 is for illustrative purposes only and is in no way intended as a limitation on this disclosure or its application.

(15) An example blade 20 is shown in FIG. 2A. The blade 20 includes a platform 24 supported by a root 22, which is secured to a rotor, for example. An airfoil 26 extends radially outwardly from the platform 24 opposite the root 22 to a tip 28. While the airfoil 26 is disclosed as being part of a turbine blade 20, it should be understood that the disclosed airfoil can also be used as a vane.

(16) Referring to FIG. 2B, the airfoil 26 includes an exterior airfoil surface 38 extending in a chord-wise direction C from a leading edge 30 to a trailing edge 32. The airfoil 26 is provided between pressure and suction sides 34, 36 in an airfoil thickness direction T, which is generally perpendicular to the chord-wise direction C. Multiple airfoils 26 are arranged circumferentially in a circumferential direction H. The airfoil 26 extends from the platform 24 in a radial direction R to the tip 28. The exterior airfoil surface 38 may include multiple film cooling holes.

(17) An example core for making the airfoil 26 is illustrated in FIG. 3A. The core may be a single, unitary core or include multiple core portions secured to one another. The shapes of the core portions correspond to shapes of internal cooling passages of the airfoil 26. In the example shown, the core is provided by a first core 40 constructed from ceramic and a second core 72 constructed from a refractory metal.

(18) The first core 40 includes first, second and third core portions 42, 44, 46, which all extend generally in the radial direction. An inlet core portion 54 interconnects the first, second and third core portions 42, 44, 46 at the root 22. In the example, the first core portion 42 is located near the leading edge 30 of the airfoil 26. The first core portion 42 extends in the chord-wise direction to provide a tip flag portion 58 adjacent to the tip 28. The tip flag portion 58 terminates in a first end 60 that is configured to extend beyond the trailing edge 32 of the airfoil 26 for casting purposes, which will be discussed in more detail relative to FIG. 3B.

(19) With continuing reference to FIG. 3A, the second core portion 44 terminates in a second end 62 adjacent to and radially beneath the tip flag portion 58. A first core tie 64 interconnects the second end 62 to the tip flag portion 58. The first core tie 64 provides stability of the second end 62 relative to the tip flag portion 58 as well as provides a corresponding dirt purge feature (or passage) for the airfoil 26.

(20) In the example, the first and second core portions 42, 44 provide a single radial run. The third core portion 46 is arranged between the first and second core portions 42, 44 in the chord-wise direction. The third core portion 46 has a serpentine shape providing multiple radial runs and terminates in a third end 66 near the tip flag portion 58. A second core tie 68 interconnects the third end 66 to the tip flag portion 58.

(21) Referring to FIGS. 3A and 3B, the second core portion 44 includes a slot 70 for receiving the trailing edge core portion 72. The trailing edge core portion 72 includes multiple apertures 74, which provide correspondingly shaped pedestals 88, discussed below relative to FIGS. 4A and 4B. The trailing edge core portion 72 is designed to extend beyond the exterior airfoil surface 38 (FIG. 3A) such that the trailing edge core portion 72 provides a core edge 84 that is received and held between first and second mold portions 78, 80 of a mold 76. The first and second mold portions 78, 80 provide a mold cavity 82 that receives wax that provides a shape of the airfoil 26.

(22) The second core portion 44 and trailing edge core portion 72 interface is shown in more detail in FIG. 3C. The slot 70 is provided by first and second lateral surfaces 100, 102 that are connected by an interior surface 104. In the example, the first lateral surface 100 is at a right angle to the interior surface 104. The second lateral surface 102 is at an angle 132 relative to a plane 126 that is normal to the interior surface 104. In the example, the angle 132 is less than 5 degrees, and in one example, about 3 degrees.

(23) During assembly, the slot 70 is filled with an adhesive material 134. An end 110 of the trailing edge core portion 72 is inserted into the slot 70 and abuts the interior surface 104. The first lateral surface 100 is used to align the trailing edge core portion 72 with respect to the second core portion 44 such that a first side 112 is generally parallel to the first lateral surface 100. The angled second lateral surface 102 provides relief with respect to a second side 114 of the trailing edge core portion 72 to facilitate insertion of the end 110 and accommodate the adhesive material 134 as the end 110 is seated within the slot 70.

(24) Since the second core portion 44 is constructed from a ceramic material, which is brittle, the structure may fracture during assembly or casting. The trailing edge core portion 72 includes a core width 116 between the first and second sides 112, 114. The second core portion 44 includes first and second outer lateral surfaces 118, 120 that respectively adjoin the first and second exterior surfaces 106, 108. The first exterior surface 106 includes a first width 118 that is approximately 1.5 times the core width 116. A second width 120 is provided between the plane 126 and along the second exterior surface 108. The second width 120 is approximately 1.5 times the core width 116.

(25) The slot 70 has first and second gap widths 122, 124, which are approximately one-quarter the core width 116. The slot 70 extends a depth 128 that is at least approximately 0.050 inch (1.27 mm). The second core portion 44 has a length 130 of structure beneath the slot 70 that is at least 0.050 inch (1.27 mm).

(26) Referring to FIG. 3D, the trailing edge core portion 72 includes a region 136 with a first radius 138 that is without holes to provide additional strength at an edge 142 of the trailing edge core portion 72 where the trailing edge core portion 72 is received within the slot 70. Additionally, the corner of the trailing edge core portion 72 includes a second radius 140 that is roughly tangential to an edge 142 of the second core portion 44. In one example, the first radius 138 is at least 0.075 inch (1.91 mm), and the second radius 140 is at least 0.050 inch (1.27 mm).

(27) Referring to FIGS. 4A and 4B and FIG. 5, the airfoil 26 includes first, second and third cooling passages 48, 50, 52 that respectively correspond to the shape of the first, second and third core portions 42, 44, 46. A trailing edge cooling passage 86 is provided in the airfoil 26 that corresponds to the shape of the trailing edge core portion 72. As shown in FIG. 4B, the apertures 74 provided in the trailing edge core portion 72 produce pedestals 88a, 88b, 88c, 88d that interconnect pressure and suction side walls 92, 94 providing desired cooling characteristics along the trailing edge 32 of the airfoil 26. The trailing edge cooling passage 86 has a thickness 90 in the range of 0.008 to 0.020 inch (0.20 to 0.51 mm).

(28) Referring to FIG. 5, the second core portion 44 terminates in the third end 66, as previously described, to provide the second cooling passage 50. Typically, the dirt accumulating in the second cooling passage 50 would be forced to exit the trailing edge cooling passage 86, which is relatively narrow and obstructed by pedestals 88 (FIG. 4B). With the second core tie 68 interconnecting the second core portion 44 and the tip flag portion 58, a dirt purge feature or passage 98 is provided, which permits the dirt in the second cooling passage 50 to instead exit through the tip flag passage 96 rather than the trailing edge cooling passage 86. As such, the tip flag passage 96 is otherwise discrete from the trailing edge cooling passage 86.

(29) Referring to FIG. 6, the trailing edge core portion 72 is illustrated with one example repeating hole pattern, which enables low cost stamping while minimizing pressure loss upstream of the trailing edge in the finished airfoil. The pedestals are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes. The trailing edge core portion 72 is constructed from a refractory metal and is relatively flat from the inner platform to the tip with very little aerodynamic twist.

(30) In the example, first, second, third and fourth holes 144, 146, 148, 150 are arranged within a repeating pattern with respect to a given hole size and amongst adjacent holes of differing sizes. In one example, the first holes 144 have a first spacing 152 in the radial direction R, and the second holes 146 have a second spacing 154 in the radial direction R. The first spacing 152 is approximately twice that of the second spacing 154. In one example, the first holes 144 are approximately twice the diameter of the second holes 146.

(31) The column of first holes 144 is adjacent to the edge 142 of the second core portion 44 at a third spacing 156 that is approximately 1.1 times the diameter of the first holes 144. The first holes 144 are spaced from the first row of second holes 146 a fourth spacing 158 that is 1.5 times the diameter of the first holes 144. The columns of second holes 146 are spaced apart from one another 2.5 times the diameter of the second holes 146, as indicated by a fifth spacing 160. The column of third holes 148 are spaced a sixth spacing 162 that is 2.5 times the diameter of the third holes 148, and the fourth holes 150 are spaced a seventh spacing 164 that is 1.5 times the diameter of the fourth holes from the trailing edge 32. The third, fourth, fifth, sixth and seventh spacings 156, 158, 160, 162, 164 are in the chordwise direction C.

(32) The fourth holes 150 are of a slightly larger diameter than the third holes 148. The third and fourth holes are approximately two-thirds the diameter of the first hole 144. In one example, the diameter of the first hole 144 is about 0.030 inch (0.76 mm).

(33) Referring to FIG. 4B, multiple pedestals having different diameters are illustrated. The first pedestal 88a corresponds to the first hole 144, the second pedestal 88b corresponds to the second hole 146, the third pedestal 88c corresponds to the third hole 148, and the fourth pedestal 88d corresponds to the fourth hole 150.

(34) Although example embodiments have been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.