Flowpath boundary and rotor assemblies in gas turbines

Patent metadata

Field	Value
Publication number	US-2016186594-A1
Application number	US-201414587768-A
Country	US
Kind code	A1
Filing date	Dec 31, 2014
Priority date	Dec 31, 2014
Publication date	Jun 30, 2016
Grant date	—

Abstract

A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

First claim

We claim:

1 . A gas turbine that includes a flowpath having a rotor assembly, the rotor assembly comprising:
a rotor wheel supporting a rotor blade, the rotor blade comprising a platform that defines an axial section of an inner boundary of the flowpath; an annulus filler residing adjacent to the rotor blade, the annulus filler comprising an outboard surface that defines an adjacent axial section of the inner boundary of the flowpath, wherein the rotor wheel comprises a connector for axially engaging both a mating surface formed on a radially innermost face of the rotor blade and a mating surface formed on a radially innermost face of the annulus filler; and an axial retainer formed between the annulus filler and the rotor wheel for axially retaining the rotor assembly against movement in at least one of a forward axial direction and an aftward axial direction; wherein the axial retainer comprises an elongated radial protruding rib formed on the annulus filler that engages a mating groove formed on the rotor wheel.

2 . The gas turbine according to claim 1 , wherein the rib and the mating groove comprise corresponding cross-sectional shapes; and
wherein the rib and mating groove comprise an axial orientation.

3 . The gas turbine according to claim 1 , wherein the connector comprises an axially engaged dovetail slot formed through the rotor wheel; and
wherein the mating surface on the each of the rotor blade and the annulus filler comprises an axially engaged dovetail configured for slidably engaging the dovetail slot.

4 . The gas turbine according to claim 3 wherein the dovetail and dovetail slot comprise multiple corresponding pressure faces for preventing relative radial movement therebetween; and
wherein the dovetails of the rotor blade and the annulus filler comprise a common axis upon installation; and
wherein the dovetail and dovetail slot comprise one of: a parallel configuration relative to a central axis of the gas turbine; and a tangentially canted configuration relative to the central axial of the gas turbine.

5 . The gas turbine according to claim 3 , wherein the dovetail slot extends between a profiled dovetail opening formed on each axial face of the rotor wheel and into the rim of the first rotor wheel; and
wherein a cross-section of the dovetail of each of the first rotor blade and the annulus filler corresponds to the profiled dovetail opening formed on the axial faces of the rotor wheel.

6 . The gas turbine according to claim 5 , wherein the mating groove elongates substantially axially across a floor of the dovetail slot.

7 . The gas turbine according to claim 6 , wherein the floor of the dovetail slot comprise an innermost radial surface of the dovetail slot.

8 . The gas turbine according to claim 7 , wherein the mating groove comprises a substantially constant cross-sectional shape and extends from a forward axial face of the rotor wheel and terminates at a terminating face that is positioned within the aftward portion of the rotor wheel.

9 . The gas turbine according to claim 8 , wherein the terminating face of the groove resides near an aft axial face of the rotor wheel.

10 . The gas turbine according to claim 8 , wherein the rib on the annulus filler is configured so to include a contact face; and
wherein the contact face of the rib and the terminating face of the mating groove are configured so to radially overlap.

11 . The gas turbine according to claim 10 , wherein the terminating face and the contact face cooperate so to arrest continued axial movement of the annulus filler in the aftward axial direction once the annulus filler is slid along the dovetail slot so to attain an installed position.

12 . The gas turbine according to claim 7 , wherein the mating groove comprises a substantially constant cross-sectional shape and extends from an aft axial face of the rotor wheel and terminates at a terminating face that is positioned within the forward portion of the rotor wheel.

13 . The gas turbine according to claim 12 , wherein the terminating face of the mating groove resides near a forward axial face of the rotor wheel.

14 . The gas turbine according to claim 12 , wherein the rib on the annulus filler is configured so to include a contact face; and
wherein the contact face of the rib and the terminating face of the mating groove are configured so to radially overlap.

15 . The gas turbine according to claim 14 , wherein the terminating face and the contact face cooperate so to arrest continued axial movement of the annulus filler in the forward axial direction once the annulus filler is slid along the dovetail slot so to attain an installed position.

16 . The gas turbine according to claim 11 , wherein the rib projects radially inward from an innermost surface of the dovetail of the annulus filler; and
wherein the rib is positioned toward the forward end of the dovetail of the annular filler.

17 . The gas turbine according to claim 11 , wherein the rib is configured so to extend between a forward end and an aft end;
wherein the forward end resides adjacent to a forward face of the dovetail of the annulus filler; and wherein the aft end comprises the contact face of the rib and resides near an axial midpoint of the dovetail of the annulus filler.

18 . The gas turbine according to claim 11 , wherein the rotor wheel comprises a first rotor wheel, the rotor blade comprises a first rotor blade, and the axial section comprises a first axial section of the inner boundary of the flowpath;
wherein a second rotor wheel supports a second rotor blade, the second rotor blade comprising a platform that defines a second axial section of the inner boundary of the flowpath; wherein the adjacent axial section comprises a third axial section of the inner boundary of the flowpath, the third axial section positioned between the first axial section and the second axial section; and wherein, relative an expected direction of flow of a working fluid through the flowpath during operation of the gas turbine, the first axial section comprises an upstream axial section and the second axial section comprises a downstream axial section of the inner boundary of the flowpath, and the third axial section comprises a middle axial section of the inner boundary of the flowpath disposed therebetween.

19 . The gas turbine according to claim 18 , wherein the gas turbine comprises a compressor operably linked to a turbine, and the flowpath comprises a compressor flowpath; and
wherein the first rotor blade and the annulus filler comprise separate, non-integrally formed components relative to each other.

20 . The gas turbine according to claim 18 , wherein the dovetail and dovetail slot comprise multiple corresponding pressure faces for preventing relative radial movement therebetween;
wherein the dovetails of the first rotor blade and the annulus filler comprise a common axis upon installation; and the rib comprises a cross-sectional shape including one of: semi-circular, triangular, and rectangular.

21 . The gas turbine according to claim 18 , wherein the first rotor blade and the second rotor blade define a circumferential extending annulus gap therebetween; and
wherein the annulus gap is defined: along an upstream gap face by a root of the first rotor blade; along a downstream gap face by a root of the second rotor blade; along an inboard floor by the rim of the first rotor wheel; and along an outboard ceiling by a reference plane ex

Assignees

• Gen Electric

Inventors

• Healy Michael James
• Leary Brendon James

Classifications

• F01D5/326

  Locking of axial insertion type blades by other means · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F05D2240/24

  for turbines · CPC title