DAMPER PIN FOR DAMPING ADJACENT TURBINE BLADES

A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.

Fixture and method for installing turbine buckets

A fixture and method for installing turbine buckets is disclosed. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots, the fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto.

SLOTTED DAMPER PIN FOR A TURBINE BLADE

A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the elongated body that is configured to contact with a groove defined between the adjacent turbine blades. The elongated body includes a first side portion laterally opposed to a second side portion and defines a plurality of laterally extending slots. The slots are axially spaced along the center portion and each slot extends at least partially through at least one of the first side portion or the second side portion. 1. A damper pin for damping adjacent turbine blades coupled to a rotor shaft , the damper pin comprising:an elongated body having a center portion disposed between a first end portion and a second end portion, the first end portion, center portion and second end portion defining a generally arcuate top portion of the elongated body configured to contact with a groove defined between the adjacent turbine blades, wherein the elongated body includes a first side portion laterally opposed to a second side portion;wherein the elongated body defines a plurality of laterally extending slots axially spaced along the center portion, wherein each slot extends at least partially through at least one of the first side portion or the second side portion.2. The damper pin as in claim 1 , wherein the plurality of slots comprises a first set of slots that extend through the first side portion of the elongated body and a second set of slots that extend through the second side portion of the elongated body.3. The damper pin as in claim 2 , wherein each slot of the first set of slots is axially offset from an axially adjacent slot of the second set of slots.4. The damper pin as in claim 1 , wherein at least one slot of the plurality of slots extends through the top portion and ...

ROTATING AIRFOIL COMPONENT OF A TURBOMACHINE

A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing. 1. A rotating airfoil component of a turbomachine , the component comprising:an airfoil adapted for impingement by a working fluid of the turbomachine;means for mounting the component to a rotating component of the turbomachine to enable rotation of the component within the turbomachine; andat least one angel wing projecting from the component and adapted to inhibit flow of the working fluid from the airfoil toward the mounting means of the component, the angel wing having a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting means, at least one lateral surface therebetween, and a thermal-insulating coating system on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.2. The rotating airfoil component according to claim 1 , wherein the turbomachine is a gas turbine engine claim 1 , the component is a bucket claim 1 , and the working fluid is combustion gases.3. The rotating airfoil component according to claim 1 , wherein the coating system comprises a ceramic coating.4. The rotating ...

SYSTEM AND METHOD FOR COOLING TURBINE BLADES

A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade. 1. A system , comprising: an entrance coupled to the interior;', 'a converging section downstream from the entrance, wherein the converging section comprises a first cross-sectional area that decreases in the flow direction; and', 'an exit disposed along a trailing edge of the turbine blade., 'a turbine blade comprising at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade, wherein the cooling slot comprises2. The system of claim 1 , comprising a metering section downstream from the converging section claim 1 , wherein the metering section comprises a second cross-sectional area that is substantially constant in the flow direction.3. The system of claim 2 , wherein the converging section comprises a first length in the flow direction claim 2 , the metering section comprises a second length in the flow direction claim 2 , and the first length is greater than the second length.4. The system of claim 1 , wherein the exit is not disposed on a pressure side or a suction side of the turbine blade.5. The system of claim 1 , wherein the exit is disposed along a midline of the trailing edge.6. The system of claim 1 , wherein the converging section comprises a height and a width claim 1 , wherein both the height and the width decrease in the flow direction.7. The system of claim 6 , wherein the height and the width are different from one another.8. The system of claim 1 , comprising an expanding section downstream from ...

FIXTURE AND METHOD FOR INSTALLING TURBINE BUCKETS

A fixture and method for installing turbine buckets is disclosed. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots, the fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto. 1. A fixture adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel , the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots , the fixture comprising:a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel, wherein the turbine bucket holder defines a bucket holder dovetail slot having a profile that is configured to receive and secure therein a dovetail of one of the turbine buckets, wherein the profile of the bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer thereto from the spacer wheel, wherein the dovetail of the turbine bucket substantially aligns with a dovetail slot of the rotor wheel upon being secured in the bucket holder dovetail slot, a sidewall of the turbine bucket holder cooperatively engages a sidewall of a circumferentially adjacent turbine bucket holder, and wherein the dovetail of the turbine bucket is slidably removable from the bucket holder dovetail slot and guided for insertion into the dovetail slot of the rotor wheel.2. The ...

Turbine bucket airfoil profile

A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

TURBOMACHINE BLADE WITH TIP FLARE

Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane. 1. A system , comprising: 'a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade comprises a blade base portion and a flared blade tip portion flared relative to the blade base portion, wherein a trailing edge of each turbomachine blade extends along a common plane.', 'a turbomachine, comprising2. The system of claim 1 , wherein the flared blade tip portion is flared away from the trailing edge of the blade base portion.3. The system of claim 1 , wherein the flared blade tip portion is flared at least partially in an axial direction relative to a rotational axis of the turbomachine.4. The system of claim 1 , wherein the flared blade tip portion is flared at least partially in a circumferential direction relative to a rotational axis of the turbomachine.5. The system of claim 1 , wherein the flared blade tip portion is flared in an axial direction and a circumferential direction relative to a rotational axis of the turbomachine.6. The system of claim 1 , wherein the common plane is at least partially defined by a mean camber line of each turbomachine blade at the trailing edge of each turbomachine blade.7. The system of claim 6 , wherein the mean camber line of each turbomachine blade at the trailing edge of each turbomachine blade is defined by a spanwise average of each turbomachine blade at the trailing edge.8. The system of claim 1 , wherein the turbomachine comprises a gas turbine.9. The system of claim 1 , wherein the flared blade tip portion is flared away from the trailing edge of the blade base portion claim 1 , the flared blade tip portion is flared at least ...

System and method for cooling turbine blades

A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.

TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL

According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life.

TURBINE BUCKET AIRFOIL PROFILE

A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Damper pin having elongated bodies for damping adjacent turbine blades

A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.

TURBINE ASSEMBLY

According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.

Turbine assembly

According to one aspect of the invention, a turbine assembly includes an airfoil extending from a blade and a dovetail located on a lower portion of the blade, wherein the dovetail has a dovetail contact surface. The turbine assembly also includes a member with a slot configured to couple to the airfoil via the dovetail, the slot having a slot contact surface to contact the dovetail contact surface, wherein the dovetail contact surface is reduced by a relief to alter a fundamental frequency of an assembly of the blade and member.

Rotating airfoil component of a turbomachine

A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.

Turbomachine blade with tip flare

Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.

Turbomachine blade with tip flare

Fixture and method for installing turbine buckets

A fixture (400) and method for installing turbine buckets (300) is disclosed. The fixture (400) is adapted for mounting a plurality of turbine buckets with dovetails (112) to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel (200), the rotor wheel and the spacer wheel (200) each having a plurality of circumferentially aligned dovetail slots (202), the fixture (100, 400) includes: a turbine bucket (300) holder having a dovetail (112) that is configured to engage with one of the dovetail slots (202) of the spacer wheel (200). The profile of a bucket holder dovetail slot (202) substantially aligns the dovetail (112) of the turbine bucket (300) with a dovetail slot (202) of the rotor wheel for at least partial transfer of a turbine bucket (300) thereto.

Damper pin for turbine blades and corresponding turbine engine

A damper pin 100 for damping adjacent turbine blades 28 coupled to a rotor shaft 24 includes an elongated body 102 having a center portion 104 disposed between a first end portion 106 and a second end portion 108. The first end portion 106, center portion 104 and second end portion 108 define a generally arcuate top portion 110 of the elongated body 102 that is configured to contact with a groove 48 defined between the adjacent turbine blades 28. The elongated body 102 includes a first side portion 112 laterally opposed to a second side portion 114 and defines a plurality of laterally extending slots 116. The slots 116 are axially spaced along the center portion 104 and each slot 116 extends at least partially through at least one of the first side portion 112 or the second side portion 114.