Patent Application
20140271206
The present disclosure generally pertains to gas turbine engines, and is more particularly directed toward a turbine blade with a pin seal slot.
Gas turbine engines include compressor, combustor, and turbine sections. Turbine sections include turbine blades with adjacent slash faces. Heated air or gases from the combustor may pass through a gap between the slash faces, increasing the operating temperature of turbine components.
U.S. Pat. No. 8,137,072 to H. Kim discloses a turbine blade. The turbine blade may have an airfoil extending from a first surface of a turbine platform. The turbine blade may further have a first side pocket of the turbine platform that is configured to substantially entirely house a first moveable seal between a forward wall of the first side pocket and an aft wall of the first side pocket. The first side pocket may have a convex surface, extending between the forward wall and the aft wall, and a concave surface. The turbine blade may also have a second side pocket of the turbine platform configured to receive a portion of a second moveable seal.
The present disclosure is directed toward overcoming one or more of the problems discovered by the inventors.
A turbine blade for a gas turbine engine having a turbine disk with an axis is disclosed. The turbine blade includes an airfoil, a blade root, and a platform. The airfoil extends in a first direction. The airfoil includes a leading edge, a trailing edge, a pressure side spanning between the leading edge and the trailing edge, and a suction side spanning between the leading edge and the trailing edge. The blade root extends in a second direction, opposite the first direction. The platform is located between the airfoil and the blade root. The platform includes a forward end adjacent the leading edge and an aft end adjacent the trailing edge. The platform also includes a pressure side platform extending from the pressure side and a suction side platform extending from the suction side in a direction opposite the pressure side platform. The pressure side platform includes a pressure side slash face distal to the pressure side and a pressure side seal slot. The pressure side slash face extends from the forward end to the aft end. The pressure side seal slot extends into the pressure side platform from the pressure side slash face. The pressure side seal slot is angled between three and ten degrees in a radial direction relative to a reference axis located below the blade root, opposite the airfoil. The reference axis is coaxial to the axis of the turbine disk when the turbine blade is installed onto the turbine disk. The pressure side seal slot is angled with a forward portion of the pressure side seal slot being radially closer to the reference axis than an aft portion of the pressure side seal slot. The suction side platform includes a suction side slash face distal to the suction side and a suction side seal slot. The suction side slash face extends from the forward end to the aft end. The suction side seal slot extends into the suction side platform from the suction side slash face. The suction side seal slot is angled between three and ten degrees in the radial direction relative to the reference axis with a forward portion of the suction side seal slot being radially closer to the reference axis than an aft portion of the suction side seal slot.
The systems and methods disclosed herein include a turbine disk assembly. In embodiments, the turbine disk assembly includes a turbine disk, turbine blades, and a pin seal. Each turbine blade includes a pressure side seal slot in the pressure side slash face, and a suction side seal slot in the suction side slash face. The pressure side seal slot includes a pressure side sealing surface and the suction side seal slot includes a suction side sealing surface. The pressure side seal slot of a first turbine blade and the suction side seal slot of a second turbine blade, adjacent the first turbine blade, combine to form a seal slot. A pin seal is retained within each seal slot. During operation of the gas turbine engine, each pin seal is located adjacent and in contact with a pressure side sealing surface and a suction side sealing surface. Air or gases heated from the combustion reaction may pass between adjacent pressure side and suction side slash faces. The air may impinge and increase the operating temperature of the disk posts of the turbine disk. The pin seals may block, reduce, or redirect the heated air, which may reduce the operating temperature of the disk posts, increasing the creep life of the turbine disk. The angle between the pressure side sealing surface and the suction side sealing surface may be between ninety-five degrees and one-hundred fifteen degrees, which may reduce possible binding between the pin seal and adjacent turbine blades and facilitate equal distribution of contact loading between the pressure side sealing surface and the suction side sealing surface. The seal slot may be angled in the radial direction relative to the turbine disk axis, which may facilitate lengthening the pin seal, increasing the contact area between the pin seal and both the pressure side sealing surface and the suction side sealing surface.
In addition, the disclosure may generally reference a center axis 95 of rotation of the gas turbine engine, which may be generally defined by the longitudinal axis of its shaft 120 (supported by a plurality of bearing assemblies 150). The center axis 95 may be common to or shared with various other engine concentric components. All references to radial, axial, and circumferential directions and measures refer to center axis 95, unless specified otherwise, and terms such as “inner” and “outer” generally indicate a lesser or greater radial distance from, wherein a radial 96 may be in any direction perpendicular and radiating outward from center axis 95.
A gas turbine engine 100 includes an inlet 110, a shaft 120, a gas producer or “compressor” 200, a combustor 300, a turbine 400, an exhaust 500, and a power output coupling 600. The gas turbine engine 100 may have a single shaft or a dual shaft configuration.
The compressor 200 includes a compressor rotor assembly 210, compressor stationary vanes (“stators”) 250, and inlet guide vanes 255. The compressor rotor assembly 210 mechanically couples to shaft 120. As illustrated, the compressor rotor assembly 210 is an axial flow rotor assembly. The compressor rotor assembly 210 includes one or more compressor disk assemblies 220. Each compressor disk assembly 220 includes a compressor rotor disk that is circumferentially populated with compressor rotor blades. Stators 250 axially follow each of the compressor disk assemblies 220. Each compressor disk assembly 220 paired with the adjacent stators 250 that follow the compressor disk assembly 220 is considered a compressor stage. Compressor 200 includes multiple compressor stages. Inlet guide vanes 255 axially precede the first compressor stage.
The combustor 300 includes one or more injectors 350 and includes one or more combustion chambers 390.
The turbine 400 includes a turbine rotor assembly 410, and turbine nozzles 450. The turbine rotor assembly 410 mechanically couples to the shaft 120. As illustrated, the turbine rotor assembly 410 is an axial flow rotor assembly. The turbine rotor assembly 410 includes one or more turbine disk assemblies 420. Each turbine disk assembly 420 includes a turbine disk 422 (shown in
The exhaust 500 includes an exhaust diffuser 520 and an exhaust collector 550.
Each turbine blade 460 includes a platform 463, an airfoil 461, and a blade root 462. Airfoil 461 extends outward, in a first direction, from platform 463 forming a leading edge 458 (see
Blade root 462 extends inward from platform 463, in a second direction, in the direction opposite airfoil 461 or opposite the first direction. When turbine blade 460 is installed in turbine disk 422, blade root 462 extends in the radially inward direction from platform 463. Blade root 462 is the parent component attachment piece and is configured to insert into a turbine disk slot 423. Blade root 462 may have a fir tree or a dovetail shape.
Platform 463 includes a pressure side platform 473 extending out from pressure side 471 and a suction side platform 483 extending out from suction side 481 in the direction opposite pressure side platform 473. When turbine blade 460 is installed in turbine disk 422, pressure side platform 473 extends in a first circumferential direction relative to the axis of turbine disk 422 and suction side platform 483 extends in a second circumferential direction, opposite the first circumferential direction, relative to turbine disk 422.
Pressure side platform 473 includes pressure side slash face 472. Pressure side slash face 472 is the surface at the end of pressure side platform 473 and is distal to airfoil 461. Pressure side slash face 472 may be angled relative to the direction pressure side platform 473 extends. In one embodiment, pressure side slash face 472 is perpendicular to the direction of pressure side platform 473. In another embodiment, pressure side slash face 472 is angled between zero and forty-five degrees from the direction perpendicular to the direction of pressure side platform 473.
Suction side platform 483 includes suction side slash face 482. Suction side slash face 482 is the surface at the end of suction side platform 483 and is distal to airfoil 461. Suction side slash face 482 Suction side slash face 482 may be angled relative to the direction suction side platform 483 extends. In one embodiment, suction side slash face 482 is perpendicular to the direction of suction side platform 483. In another embodiment, suction side slash face 482 is angled between zero and forty-five degrees from the direction perpendicular to the direction of suction side platform 483.
When adjacent turbine blades 460 are installed onto turbine disk 422 the pressure side slash face 472 of a first turbine blade is adjacent to the suction side slash face 482 of a second turbine blade. Pressure side slash face 472 may be parallel to suction side slash face 482. Pressure side slash face 472 of the first turbine blade and suction side slash face 482 of the second turbine blade are configured to form a slash face gap 497 there between.
Referring to
Pressure side platform 473, forward pressure side damper buttress 476, and aft pressure side damper buttress 477 may be configured to form pressure side underplatform pocket 475. Pressure side platform 473 may include pressure side underplatform surface 498 adjacent pressure side underplatform pocket 475, forward pressure side damper buttress 476 may include forward pressure damper surface 491 adjacent pressure side underplatform pocket 475, and aft pressure side damper buttress 477 may include aft pressure damper surface 492 adjacent pressure side underplatform pocket 475. Aft pressure damper surface 492 may be parallel to forward pressure damper surface 491 and perpendicular to pressure side underplatform surface 498. Aft pressure damper surface 492 faces forward pressure damper surface 491, and forward pressure damper surface 491 faces aft pressure damper surface 492.
Suction side platform 483, forward suction side damper buttress 486, and aft suction side damper buttress 487 may be configured to form suction side underplatform pocket 485. Suction side platform 483 may include suction side underplatform surface 499 adjacent suction side underplatform pocket 485, forward suction side damper buttress 486 may include forward suction damper surface 493 adjacent suction side underplatform pocket 485, and aft suction side damper buttress 487 may include aft suction damper surface 494 adjacent suction side underplatform pocket 485. Aft suction damper surface 494 may be parallel to forward suction damper surface 493 and perpendicular to suction side underplatform surface 499. Aft suction damper surface 494 faces forward suction damper surface 493, and forward suction damper surface 493 faces aft suction damper surface 494.
Referring to
Each turbine blade 460 includes a pressure side seal slot 474 and a suction side seal slot 484. Adjacent turbine blades 460 are also configured to form seal slot 464 with a pressure side seal slot 474 of a first turbine blade and the adjacent suction side seal slot 484 of a second turbine blade. Referring to
Aft pressure side slot 479 extends into pressure side platform 473 from pressure side slash face 472 below the trailing edge 459, adjacent to aft pressure side damper buttress 477, and above aft pressure side damper buttress 477. Aft pressure side slot 479 includes aft pressure side surface 442. Aft pressure side surface 442 is distal to leading edge 458 and is the end surface of pressure side seal slot 474 farthest from leading edge 458. Aft pressure side surface 442 may have a planar or a rounded surface, and may round into the concave shape of aft pressure side slot 479. Aft pressure side slot 479 may have a concave shape and spans from pressure side underplatform pocket 475 to aft pressure side surface 442.
Pressure side sealing surface 495 spans between forward pressure side surface 441 to aft pressure side surface 442, the length of pressure side seal slot 474. Pressure side sealing surface 495 may be a planar surface angling into pressure side platform 473 from pressure side slash face 472. Forward pressure side slot 478 may include the forward portion of pressure side sealing surface 495. Aft pressure side slot 479 may include the aft portion of pressure side sealing surface 495. The portion of pressure side sealing surface 495 between forward pressure side slot 478 and aft pressure side slot 479 may angle into pressure side platform 473 to pressure side underplatform pocket 475.
Pressure side seal slot 474 may span along pressure side slash face 472 at an angle with forward pressure side slot 478 angled toward forward end 466 and in the direction that blade root 462 extends from platform 463, and with aft pressure side slot 479 angled toward aft end 467 and in the direction that airfoil 461 extends from platform 463. Pressure side seal slot 474 may be angled relative to a reference axis. The reference axis is coaxial to the axis of turbine disk 422 when turbine blade 460 is installed onto turbine disk 422 and is coaxial to center axis 95 (shown in
Pressure side seal slot 474 may be angled in the radial direction relative to the reference axis with forward pressure side slot 478 being closer to the reference axis than aft pressure side slot 479. Angle 87 is the angle of pressure side seal slot 474 relative to the reference axis. Reference line 85 is shown to illustrate angle 87. Reference line 85 is parallel to the reference axis and is shifted radially outward from the reference axis. In one embodiment, pressure side seal slot 474 is angled relative to the reference axis in the radial direction between three and ten degrees. In another embodiment, pressure side seal slot 474 is angled relative to the reference axis in the radial direction from four to six degrees. In yet another embodiment, pressure side seal slot 474 is angled relative to the reference axis in the radial direction at five degrees, approximately five degrees, or within a predetermined tolerance of five degrees.
Pressure side sealing surface 495 spans along pressure side slash face 472 at an angle with the forward portion of pressure side sealing surface 495 being angled toward forward end 466 and in the direction that blade root 462 extends from platform 463, and with the aft portion of pressure side sealing surface 495 being angled toward aft end 467 and in the direction that airfoil 461 extends from platform 463.
Pressure side sealing surface 495 may be angled relative to the reference axis. Angle 87 also illustrates the angle of pressure side sealing surface 495 relative to the reference axis. Pressure side sealing surface 495 may be angled in the radial direction relative to the reference axis with the forward portion of pressure side sealing surface 495 being closer to the reference axis than the aft portion of pressure side sealing surface 495. In one embodiment, pressure side sealing surface 495 is angled relative to the reference axis in the radial direction between three and ten degrees. In another embodiment, pressure side sealing surface 495 is angled relative to the reference axis in the radial direction from four to six degrees. In yet another embodiment, pressure side sealing surface 495 is angled relative to the reference axis in the radial direction at five degrees, approximately five degrees, or within a predetermined tolerance of five degrees.
In the embodiment shown, pressure side sealing surface 495 is the radially outer portion of pressure side seal slot 474 relative to the reference axis.
Referring to
Aft suction side slot 489 extends into suction side platform 483 from suction side slash face 482 below the trailing edge 459, adjacent to aft suction side damper buttress 487, and above aft suction side damper buttress 487. Aft suction side slot 489 includes aft suction side surface 444. Aft suction side surface 444 is distal to leading edge 458 and is the end surface of suction side seal slot 484 farthest from leading edge 458. Aft suction side surface 444 may have a planar or a rounded surface, and may round into the concave shape of aft suction side slot 489. Aft suction side slot 489 may have a concave shape and spans from suction side underplatform pocket 485 to aft suction side surface 444.
Suction side sealing surface 496 spans between forward suction side surface 443 to aft suction side surface 444, the length of suction side seal slot 484. Suction side sealing surface 496 may be a planar surface angling into suction side platform 483 from suction side slash face 482. Forward suction side slot 488 may include the forward portion of suction side sealing surface 496. Aft suction side slot 489 may include the aft portion of suction side sealing surface 496. The portion of suction side sealing surface 496 between forward suction side slot 488 and aft suction side slot 489 may angle into suction side platform 483 to suction side underplatform pocket 485.
Suction side seal slot 484 may span along suction side slash face 482 at an angle with forward suction side slot 488 angled toward forward end 466 and in the direction that blade root 462 extends from platform 463, and with aft suction side slot 489 angled toward aft end 467 and in the direction that airfoil 461 extends from platform 463. Suction side seal slot 484 may be angled relative to the reference axis.
Suction side seal slot 484 may be angled in the radial direction of the reference axis with forward suction side slot 488 being closer to the reference axis than aft suction side slot 489. Angle 88 is the angle of suction side seal slot 484 relative to the reference axis. Reference line 85 is shown to illustrate angle 88. In one embodiment, suction side seal slot 484 is angled relative to the reference axis in the radial direction between three and ten degrees. In another embodiment, suction side seal slot 484 is angled relative to the reference axis in the radial direction from four to six degrees. In yet another embodiment, suction side seal slot 484 is angled relative to the reference axis in the radial direction at five degrees, approximately five degrees, or within a predetermined tolerance of five degrees. The angles of suction side seal slot 484 and of pressure side seal slot 474 in the radial direction relative to the reference axis of turbine disk 422 are equal or within a predetermined tolerance.
Suction side sealing surface 496 spans along suction side slash face 482 at an angle with the forward portion of suction side sealing surface 496 being angled toward forward end 466 and in the direction that blade root 462 extends from platform 463, and with the aft portion of suction side sealing surface 496 being angled toward aft end 467 and in the direction that airfoil 461 extends from platform 463. Suction side sealing surface 496 may be angled relative to the reference axis.
Suction side sealing surface 496 may be angled in the radial direction relative to the reference axis with the forward portion of suction side sealing surface 496 being closer to the reference axis than the aft portion of suction side sealing surface 496. Angle 88 also illustrates the angle of suction side sealing surface 496 relative to the reference axis. In one embodiment, suction side sealing surface 496 is angled relative to the reference axis in the radial direction between three and ten degrees. In another embodiment, suction side sealing surface 496 is angled relative to the reference axis in the radial direction from four to six degrees. In yet another embodiment, suction side sealing surface 496 is angled relative to the reference axis in the radial direction at five degrees, approximately five degrees, or within a predetermined tolerance of five degrees. The angles of suction side sealing surface 496 and of pressure side sealing surface 495 in the radial direction relative to the reference axis are equal or within a predetermined tolerance.
In the embodiment shown, suction side sealing surface 496 is the radially outer portion of suction side seal slot 484 relative to the reference axis.
Pressure side sealing surface 495 may be a planar surface angling into pressure side platform 473 from pressure side slash face 472. Pressure side sealing surface 495 may be angled from pressure side slash face 472 towards blade root 462 in the direction opposite the direction that pressure side platform 473 extends and in the same direction that blade root 462 extends. Suction side sealing surface 496 may be a planar surface angling into suction side platform 483 from suction side slash face 482. Suction side sealing surface 496 may be angled from suction side slash face 482 towards blade root 462 in the direction opposite the direction that suction side platform 483 extends and in the same direction that blade root 462 extends.
Pressure side sealing surface 495 and suction side sealing surface 496 form a roof at the top of seal slot 464. Angle 83 is the angle between pressure side sealing surface 495 and suction side sealing surface 496. In one embodiment, the angle 83 between pressure side sealing surface 495 and suction side sealing surface 496 is between ninety-five degrees and one-hundred fifteen degrees. In another embodiment, the angle 83 between pressure side sealing surface 495 and suction side sealing surface 496 is between one-hundred degrees and one-hundred ten degrees. In yet another embodiment, the angle 83 between pressure side sealing surface 495 and suction side sealing surface 496 is one-hundred five degrees or approximately one-hundred five degrees.
Pressure side sealing surface 495 and suction side sealing surface 496 may each be angled relative to a reference plane 86. The reference plane 86 is the center plane and may be the plane of symmetry extending through blade root 462. The reference plane 86 may also extend from and include the stacking axis of turbine blade 460. The reference plane 86 extends through blade root 462 from forward end 466 to aft end 467. When turbine blade 460 is installed onto turbine disk 422, the reference plane 86 is a radial plane that includes the axis of turbine disk 422 and extends from the axis through the blade root 462.
Angle 81 is the angle that pressure side sealing surface 495 is angled relative to reference plane 86. In one embodiment, pressure side sealing surface 495 is angled relative to the reference plane 86 between sixty and seventy degrees. In another embodiment, pressure side sealing surface 495 is angled relative to the reference plane 86 from sixty-four to sixty-six degrees. In yet another embodiment, pressure side sealing surface 495 is angled relative to the reference plane 86 at sixty-five degrees, at approximately sixty-five degrees or within a predetermined tolerance of sixty-five degrees.
Suction side sealing surface 496 may be angled relative to the reference plane 86 in the opposite direction of pressure side sealing surface 495. Angle 82 is the angle that suction side sealing surface 496 is angled relative to reference plane 86. In one embodiment, suction side sealing surface 496 is angled relative to the reference plane 86 between forty and fifty degrees. In another embodiment, suction side sealing surface 496 is angled relative to the reference plane 86 from forty-four to forty-six degrees. In yet another embodiment, suction side sealing surface 496 is angled relative to the reference plane 86 at forty-five degrees, at approximately forty-five degrees or within a predetermined tolerance of forty-five degrees.
During operation of gas turbine engine 100, pin seal 430 is located adjacent to and configured to contact pressure side sealing surface 495 and suction side sealing surface 496 as illustrated in
When the gas turbine engine 100 is not in operation seal slot 464 retains pin seal 430. The concave surfaces of forward suction side slot 488 (not shown in
The concave surfaces of forward pressure side slot 478 (not shown in
Referring to
Pin seal 430 is configured to extend from forward suction side slot 488 to aft suction side slot 489. When pin seal 430 is in contact with forward suction side surface 443, pin seal 430 is configured to extend beyond aft suction damper surface 494 and into aft suction side slot 489, overlapping with aft suction side damper buttress 487. When pin seal 430 is in contact with aft suction side surface 444, pin seal 430 is configured to extend beyond forward suction damper surface 493 and into forward suction side slot 488, overlapping with forward suction side damper buttress 486. In some embodiments, pin seal 430 is also configured to extend beyond leading edge 458 in the axial direction of the reference axis when pin seal 430 is in contact with aft suction side surface 444. Reference line 89 illustrates the distance that pin seal 430 extends beyond leading edge 458. Reference line 91 extends outward from an end of pin seal 430 perpendicular to the reference axis. Reference line 92 intersects the forward most point of leading edge 458 and extends parallel to reference line 91. Reference line 89 extends between reference lines 91 and 92 and is perpendicular to reference lines 91 and 92. In one embodiment, pin seal 430 extends beyond the forward most point of leading edge 458 from 0.254 mm (0.010 inches) to 0.762 (0.030 inches). In another embodiment, pin seal 430 extends beyond leading edge 458 at a minimum of 0.508 mm (0.020 inches) when pin seal 430 is in contact with aft suction side surface 444.
In one embodiment, the length of pin seal 430 is from 42.037 mm (1.655 inches) to 42.291 mm (1.665 inches). In another embodiment the length of pin seal 430 is 42.164 mm (1.660 inches) or within a predetermined tolerance of 42.164 mm (1.660 inches).
Pin seal 430 may interact with pressure side seal slot 474, forward pressure side slot 478, aft pressure side slot 479, forward pressure side damper buttress 476, aft pressure side damper buttress 477, forward pressure side surface 441, aft pressure side surface 442, forward pressure damper surface 491, and aft pressure damper surface 492 in the same or a similar manner as pin seal 430 interacts with suction side seal slot 484, forward suction side slot 488, aft suction side slot 489, forward suction side damper buttress 486, aft suction side damper buttress 487, forward suction side surface 443, aft suction side surface 444, forward suction damper surface 493, and aft suction damper surface 494 as described above.
One or more of the above components (or their subcomponents) may be made from stainless steel and/or durable, high temperature materials known as “superalloys”. A superalloy, or high-performance alloy, is an alloy that exhibits excellent mechanical strength and creep resistance at high temperatures, good surface stability, and corrosion and oxidation resistance. Superalloys may include materials such as HASTELLOY, INCONEL, WASPALOY, RENE alloys, HAYNES alloys, INCOLOY, MP98T, TMS alloys, and CMSX single crystal alloys. In embodiments, pin seal 430 is made from HAYNES 25 and turbine disk 422 is made from WASPALOY.
Gas turbine engines may be suited for any number of industrial applications such as various aspects of the oil and gas industry (including transmission, gathering, storage, withdrawal, and lifting of oil and natural gas), the power generation industry, cogeneration, aerospace, and other transportation industries.
Referring to
Once compressed air 10 leaves the compressor 200, it enters the combustor 300, where it is diffused and fuel is added. Air 10 and fuel are injected into the combustion chamber 390 via injector 350 and combusted. Energy is extracted from the combustion reaction via the turbine 400 by each stage of the series of turbine disk assemblies 420. Exhaust gas 90 may then be diffused in exhaust diffuser 520, collected and redirected. Exhaust gas 90 exits the system via an exhaust collector 550 and may be further processed (e.g., to reduce harmful emissions, and/or to recover heat from the exhaust gas 90).
Referring to
Reducing the temperature of these components, may increase the creep life and may increase the service life of these components. Referring to
Pin seal 430 may be configured to extend forward of leading edge 458 in the axial direction of the reference axis. Extending either first end 432 or second end 433 forward of leading edge 458 may block the flow path of the heated air as it enters the geometry of airfoil 461.
During operation of gas turbine engine 100 the relative positions of adjacent turbine blades 460 and pin seal 430 may shift. Binding may occur between pin seal 430 and the adjacent turbine blades 460 and pin seal 430 may become wedged between the adjacent turbine blades 460. Increasing the angles of pressure side sealing surface 495 and suction side sealing surface 496 relative to the reference plane 86 and relative to each other, such as the angles disclosed above, may prevent or reduce the possibility of binding. Increasing the angles of pressure side sealing surface 495 and suction side sealing surface 496 may also facilitate a uniform contact margin between pin seal 430 and both pressure side sealing surface 495 and suction side sealing surface 496. Increasing the angles of pressure side sealing surface 495 and suction side sealing surface 496 may help the contact load vector align with the centrifugal force load vector.
Angling pressure side sealing surface 495, suction side sealing surface 496, pressure side seal slot 474, and suction side seal slot 484 in the radial direction relative to the reference axis may facilitate the use of a longer pin seal 430. A longer pin seal 430 may increase the contact area between pin seal 430 and both pressure side sealing surface 495 and suction side sealing surface 496, which may increase the seal. A longer pin seal 430 may also reduce the centrifugal force contact loads and stress concentrations on the turbine blades 460.
Pin seal 430 does not remain affixed to turbine blade 460 during operation of gas turbine engine 100. Once gas turbine engine 100 begins to operate, the pin seal 430 centrifugal force load and the increase in temperature may break or melt the adhesive or glue, which may allow the pin seal 430 to move into the correct position adjacent and in contact with pressure side sealing surface 495 and suction side sealing surface 496.
The features in turbine blade 460 such as pressure side seal slot 474 and suction side seal slot 484 may be formed by an investment casting process that uses two or more casting block pull directions, such as compound pull casting. The features may also be formed by a machining process, such as electrical discharge machining, milling, or grinding.
The preceding detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. The described embodiments are not limited to use in conjunction with a particular type of gas turbine engine. Hence, although the present disclosure, for convenience of explanation, depicts and describes particular turbine blades and pin seals, it will be appreciated that the turbine blades and pin seals in accordance with this disclosure can be implemented in various other configurations, can be used with various other types of gas turbine engines, and can be used in other types of machines. Furthermore, there is no intention to be bound by any theory presented in the preceding background or detailed description. It is also understood that the illustrations may include exaggerated dimensions to better illustrate the referenced items shown, and are not consider limiting unless expressly stated as such.
