WO2002025066A1 - Steam-type gas turbine subassembly and method for enhancing turbine performance - Google Patents
Steam-type gas turbine subassembly and method for enhancing turbine performance Download PDFInfo
- Publication number
- WO2002025066A1 WO2002025066A1 PCT/US2001/025915 US0125915W WO0225066A1 WO 2002025066 A1 WO2002025066 A1 WO 2002025066A1 US 0125915 W US0125915 W US 0125915W WO 0225066 A1 WO0225066 A1 WO 0225066A1
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- WIPO (PCT)
- Prior art keywords
- gas
- rotor
- downstream
- flow
- stator
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/56—Brush seals
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the inventors of the present invention have developed a combination of elements for reducing the amount of the secondary flow of gas from the wheel space cavities into the main flow of gas which provides a more effective solution to the problem of gas leakage in steam-type gas turbines without introducing any new problems in place thereof.
- the first gas-flow deflector 30 is formed by an edge 24a of the stator 24 located across from and adjacent to the root 40 of the downstream stage 38 of the rotor 40.
- the second gas-flow deflector 32 is formed by an edge 40a of the root 40 of the downstream stage 38 of the rotor 26 across from the edge 24a of the stator 24 such that the first gas-flow deflector 30 is located spaced from and above the second gas-flow deflector 32 and the second gas ⁇ flow deflector 32 is slightly sloped toward the axis 34 so that the secondary flow of gas 48 from the wheel space cavity 46 into the main flow of gas 44 turns between the first and second gas-flow deflectors 30, 32 toward the downstream stage 38 of the rotor 26 and into the main flow of gas 44 into a tangential relationship to the main flow of gas 44 and to the root 40 of the downstream stage 38 of the rotor 26.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
A steam-type gas turbine subassembly (22) for enhancing the turbine performance includes a stator (24), rotor (26), annular brush seal (28) or annular labyrinth seal (56), and first and second gas-flow deflectors (30, 32). A main flow of gas (44) moves along the stator (24) and rotor (26) which together define a wheel space cavity (46). A secondary flow of gas (48) moves from the main flow of gas (44) adjacent to an upstream stage (36) of the rotor (26) through the wheel space cavity (46) and into the main flow of gas (44) adjacent to a downstream stage (38) of the rotor (26). The annular brush seal (28) or annular labyrinth seal (56) extends across the wheel space cavity (46) between the rotor stages (36, 38) blocking at least a portion of the secondary flow of gas (48). The gas-flow deflectors (36, 38) are radially displaced and offset from one another such that the secondary flow of gas (48) is turned into a tangential relationship to the main flow of gas (44).
Description
STEAM-TYPE GAS TURBINE SUBASSEMBLY
AND METHOD FOR ENHANCING TURBINE
PERFORMANCE
BACKGROUND OF THE INVENTION
The present invention generally relates to steam-type gas turbines and, more particularly, is concerned with a steam-type gas turbine subassembly and method for enhancing turbine performance.
Gas turbines include combustion-type gas turbines, which utilize combustion gases to turn rotors, and steam-type gas turbines, which utilize steam to turn rotors. Examples of gas turbines include, but are not limited to, gas-turbine power-generation equipment and gas-turbine aircraft engines. A combustion-type gas turbine has a gas path which typically includes, in serial relationship, an air intake (or inlet), a compressor, a combustor, a turbine and a gas outlet (or exhaust nozzle). A steam-type gas turbine has a gas path which typically includes, in serial relationship, a steam inlet, a turbine and a steam outlet.
Gas leakage between certain gas turbine components is undesirable because it wastes gas (e.g., air, combustion gas, steam, etc.), causing a loss in power and efficiency. For example, as shown with respect to a prior art subassembly 10 of a steam-type gas turbine in FIG. 1, such loss in power and efficiency occurs due to gas leakage, as shown by arrows A, B and C, between radially overlapping and adjacent portions of a rotor 12 and stator 14 of the subassembly 10. Means have been introduced into both combustion-type and steam-type gas turbines for reducing gas leakage. The use of labyrinth seals and brush seals in both combustion-type and steam-type gas turbines per se is known in the art, being disclosed in U.S. Pat. No. 5,613,829 to Wolfe et al. and assigned to General Electric Company, the assignee of the present invention. Gas-flow deflectors on turbine blade roots have also been used in both types of turbines. Prior art gas-flow root deflectors 15, as shown in FIG. 2, have in the past provided a transverse secondary flow of gas, as indicated by the arrow A in FIG. 2, from a wheel space cavity 16 between the stator 14 and root 16 of
turbine blade 18 of a stage 20 of the rotor 12 into a main flow of gas, as indicated by arrow D, along and past the blade 18 of the rotor 12. Combustion-type gas turbines manufactured by the General Electric Company have been designed with gas-flow root deflectors which provide a tangential and axial flows rather than the standard transverse secondary flow of gas from the wheel space cavity into the main flow of gas.
However, the tangential flow deflector design has not previously been introduced into steam-type gas turbines before the time of the present invention. The failure to introduce the tangential flow root deflectors into the steam-type gas turbines can be at least partially attributed to a difference in the perspectives of the two types of gas turbines in regard to gas leakage. The secondary flow of gas from a wheel space cavity into the main flow of gas is desirable in combustion-type gas turbines and is not desirable in steam-type gas turbines. In the combustion-type gas turbines, it is necessary to cool and purge the wheel space cavities due to high temperatures. The secondary flow of gas from a wheel space cavity into the main flow of gas is therefore a necessary evil in combustion-type gas turbines. On the other hand, in steam-type gas turbines, such cooling and purging of the wheel space cavities is not needed. Thus, it is desirable in steam-type gas turbines to reduce the secondary flow of gas from a wheel space cavity into the main flow of gas as much as possible, typically being designed for zero leakage.
Uses of steam bypass passageways and of brush seals in steam-type gas turbines to reduce the secondary flow of gas from a wheel space cavity into the main flow of gas is per se known in the art. Steam bypass passageways extend through turbine blade roots of the stages of the rotor and are open to adjacent wheel space cavities to reduce the amount of secondary flow of gas from the wheel space cavity into the main flow of gas. A problem exists, however, with steam bypass passageways in that the size of each steam bypass passageway must be optimized for the steam bypass passageway to perform with efficiency, but the optimization of the size of each steam bypass passageway is difficult to achieve. Brush seals are disposed next to the labyrinth seals in the interstage seal assemblies between stages of
the rotor. A problem exists, however, with brush seals in that they do not effectively eliminate the amount of the secondary flow of gas from the wheel space cavities into the main flow of gas.
Consequently, the inventors of the present invention have developed a combination of elements for reducing the amount of the secondary flow of gas from the wheel space cavities into the main flow of gas which provides a more effective solution to the problem of gas leakage in steam-type gas turbines without introducing any new problems in place thereof.
BRIEF SUMMARY OF THE INVENTION
The present invention provides a steam-type gas turbine subassembly and method for enhancing turbine performance which is designed to satisfy the aforementioned need. The steam-type gas turbine performance enhancing subassembly and method of the present invention is a more effective solution for the problem of gas leakage in steam-type gas turbines than has been provided by the prior art and reduces the need for optimization of the sizes of steam bypass passageways of the arrangement. The performance enhancing subassembly and method provide a unique combination of elements to reduce the amount of secondary flow of gas from wheel space cavities into a main flow of gas in the steam-type gas turbine.
In one embodiment of the present invention, a steam-type gas turbine subassembly for enhancing turbine performance comprises: a stator having a longitudinally extending axis; a rotor coaxially aligned with and disposed radially adjacent to and apart from the stator wherein the rotor includes at least a pair of stages interconnected to one another and located respectively upstream and downstream, relative to one another with each of the stages having in an annular arrangement a plurality of roots and blades mounted to the roots such that a main flow of gas moves in a path spaced radially outward from and along the longitudinally extending axis of the stator and rotor and in one direction between the blades of the adjacent upstream and downstream stages of the rotor, the stator and upstream and downstream stages of the rotor together defining at least one wheel space cavity therebetween having
opposite upstream and downstream ends open to the main flow path of gas at the upstream and downstream stages of the rotor such that at least one secondary flow of gas moves in another path through the wheel space cavity between the upstream and downstream stages of the rotor from the upstream end to the downstream end of the wheel space cavity and into the main flow of gas; at least one annular brush seal or annular labyrinth seal or both disposed between the stator and rotor and across the path of secondary flow of gas such that the brush seal blocks at least a portion of the secondary flow of gas; a first gas-flow deflector formed by an edge of the stator adjacent to the root of the downstream one of the stages of the rotor; and a second gas-flow deflector formed by an edge of the root of the downstream one of the stages of the rotor such that the first gas-flow deflector is located spaced from and above the second gas-flow deflector so that the secondary flow of gas from the wheel space cavity into the main flow of gas turns between the first and second gas-flow deflectors toward the downstream one of the stages of the rotor and into the main flow of gas in tangential relation to the main flow of gas and to the root of the downstream one of the stages of the rotor.
The subassembly further comprises at least the root of the downstream one of the stages of the rotor defining a steam bypass passageway therethrough open to the wheel space cavity and having a size adapted for diverting some of the secondary flow of gas from passing into the main flow of gas. The brush seal has an attached end and a free end. The attached end of the brush seal is mounted to the stator and the free end of the brush seal extends into the wheel space cavity toward the rotor. The annular labyrinth seal is coaxially aligned with the stator and rotor and is formed on at least one of the stator and rotor and extends into the wheel space cavity between the stator and rotor, the labyrinth seal for blocking at least a portion of the secondary flow of gas.
In another exemplary embodiment of the present invention, a steam- type gas turbine performance enhancing method comprises the steps of: providing the above-mentioned stator and rotor; introducing the above-mentioned main flow of gas; defining the above-mentioned wheel space cavity; introducing the above-mentioned
secondary flow of gas, providing at least one annular brush seal or annular labyrinth seal between the stator and rotor; and providing the above-mentioned first and second gas-flow deflectors.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a diagrammatic view of a prior art steam-type gas turbine subassembly.
FIG. 2 is an enlarged diagrammatic view of a gas-flow deflector provided at a turbine blade root of the steam-type gas turbine of FIG. 1 and producing a transverse secondary flow of gas from a wheel space cavity into a main flow of gas of the turbine.
FIG. 3 is a diagrammatic view of a steam-type gas turbine subassembly of the present invention for enhancing the turbine performance.
FIG. 4 is an enlarged diagrammatic view of the gas-flow deflector provided at the turbine blade root of the steam-type gas turbine of FIG. 3 and producing a tangential secondary flow of gas from a wheel space cavity into a main flow of gas of the turbine.
DETAILED DESCRIPTION OF THE INVENTION
Referring now to the drawings and particularly to FIG. 3, there is illustrated a steam-type gas turbine subassembly of the present invention, generally designated 22, for enhancing the turbine performance. The subassembly 22 includes a stator 24, a rotor 26, at least one annular brush seal 28, and first and second gas- flow deflectors 30, 32.
The stator 24 has a generally longitudinally extending axis 34. The rotor 26 is coaxially aligned with and disposed radially adjacent to and apart from the stator 24. The rotor 26 includes at least a pair of stages 36, 38 interconnected to one another and located respectively -upstream and downstream relative to one another along the axis 34. Each of the stages 36, 38 of the rotor 26 has, in an annular
arrangement, a plurality of roots 40 and blades 42 mounted to the roots 40. A main flow of gas 44 moves in a path spaced radially outward from and along the longitudinally extending axis 34 of the stator 24 and rotor 26 and in one direction between the blades 42 of the adjacent upstream and downstream stages 36, 38 of the rotor 26. The main flow of gas 44 is under pressure and causes the blades 42 of the stages 36, 38 of the rotor 26 to turn about the longitudinal axis 34.
The stator 24 and upstream and downstream stages 36, 38 of the rotor 26 together define at least one wheel space cavity 46 therebetween having opposite upstream and downstream ends 46a, 46b open to the main flow of gas 44, A secondary flow of gas 48 moves in another path, separate from the path of the main flow of gas 44, through the wheel space cavity 46, from the main flow of gas 44 at the upstream end 46a of the wheel space cavity 46 adjacent to the upstream stage 36 of the rotor 26 and into the main flow of gas 44 at the downstream end 46b of the wheel space cavity 46 adjacent to the downstream stage 38 of the rotor 26.
An interstage seal assembly 50 is mounted to the stator 24 and rotor 26 and extends across the wheel space cavity 46 and the secondary flow of gas 48 between the upstream and downstream stages 36, 38 of the rotor 26. As shown, the interstage seal assembly 50 includes the annular brush seal 28 of the subassembly 10 being disposed between the stator 24 and the rotor 26 and across the path of secondary flow of gas 48, however, such a brush seal is not mandatory. The brush seal 28 has an attached end 28a and a free end 28b. The attached end 28a of the brush seal 28 is mounted to the stator 24 and the free end 28b of the brush seal 28 extends into the wheel space cavity 46 toward the rotor 26. The brush seal 28 has a plurality of bristles 52. The bristles 52 define the free end 28b of the brush seal 28. The bristles 52 of the brush seal 28 extend into the wheel space cavity 46 toward the rotor
26 such that they block at least a portion of the secondary flow of gas 48 through the wheel space cavity 46 past the interstage seal assembly 50.
Referring now to FIGS. 3 and 4, the first gas-flow deflector 30 is formed by an edge 24a of the stator 24 located across from and adjacent to the root 40 of the downstream stage 38 of the rotor 40. The second gas-flow deflector 32 is
formed by an edge 40a of the root 40 of the downstream stage 38 of the rotor 26 across from the edge 24a of the stator 24 such that the first gas-flow deflector 30 is located spaced from and above the second gas-flow deflector 32 and the second gas^ flow deflector 32 is slightly sloped toward the axis 34 so that the secondary flow of gas 48 from the wheel space cavity 46 into the main flow of gas 44 turns between the first and second gas-flow deflectors 30, 32 toward the downstream stage 38 of the rotor 26 and into the main flow of gas 44 into a tangential relationship to the main flow of gas 44 and to the root 40 of the downstream stage 38 of the rotor 26. More particularly, the first and second gas-flow deflectors 30, 32 are radially displaced and offset from one another such that the second deflector 32 is spaced downstream of the first deflector 30 and located closer to the axis 34 than the first deflector 30. The tangential relationship between the secondary flow of gas 48 and the main flow of gas 44 allows the secondary flow of gas 48 to enter the main flow of gas 44 with a reduced level of disruption of the main flow of gas 44 than if the relationship between the secondary flow of gas 46 and the main flow of gas 44 were transverse. This reduced level of disruption of the main flow of gas 44 increases the power and efficiency of the gas turbine.
Referring now to FIG. 3, the subassembly 10 also includes at least the root 40 of the downstream stage 38 of the rotor 26 defining a steam bypass passageway 54 therethrough. The steam bypass passageway 54 is open to the wheel space cavity 46 for diverting at least a portion of the secondary flow of gas 48 from passing into the main flow of gas 44. The steam bypass passageway 54 has a size which is adapted to divert the portion of the secondary flow of gas 48 from passing into the main flow of gas 44. A steam bypass passageway 54 may exist in the root 40 of each of the stages 36, 38 of the rotor 26. Each steam bypass passageway 54 has opposite ends 54a, 54b open to adjacent wheel space cavities 46. A portion of the secondary flow of gas 48 may pass from one wheel space cavity 46 to the next wheel space cavity 46 through each of the steam bypass passageways 54 and thereby avoid passing into the main flow of gas 44 and so as to reduce the level of disruption of the main flow of gas 44.
As shown, the interstage seal assembly 50 of the subassembly 10 also includes at least one annular labyrinth seal 56. The labyrinth seal 56 is coaxially aligned with the stator 24 and the rotor 26. The labyrinth seal 56 is formed on at least one of the stator 24 and the rotor 26 and extends into the wheel space cavity 46 between the stator 24 and the rotor 26. The labyrinth seal 56 is for blocking at least a portion of the secondary flow of gas 44.
It is thought that the present invention and its advantages will be understood from the foregoing description and it will be apparent that various changes may be made thereto without departing from the spirit and scope of the invention or sacrificing all of its material advantages, the form hereinbefore described being merely preferred or exemplary embodiment thereof.
Claims
1. A steam-type gas turbine subassembly (22) for enhancing turbine performance, comprising:
a stator (24) having a longitudinally extending axis (34);
a rotor (26) coaxially aligned with and disposed radially adjacent to and apart from said stator (24) wherein said rotor (26) includes at least a pair of stages
(36, 38) interconnected to one another and located respectively upstream and downstream relative to one another with each of said stages (36, 38) having in an annular arrangement a plurality of roots (40) and blades (42) mounted to said roots (40) such that a main flow of gas (44) moves in a path spaced radially outward from and along said longitudinally extending axis (34) of said stator (24) and rotor (26) and in one direction between said blades (42) of said adjacent upstream and downstream stages (36, 38) of said rotor (26), said stator (24) and said upstream and downstream stages (36, 38) of said rotor (26) together defining at least one wheel space cavity (46) therebetween having opposite upstream and downstream ends (46a, 46b) open to said main flow of gas (44) at said upstream and downstream stages (36, 38) of said rotor (26) such that at least one secondary flow of gas (48) moves in another path through said wheel space cavity (46) between said upstream and downstream stages (36, 38) of said rotor (26) from said upstream end (46a) to said downstream end (46b) of said wheel space cavity (46) and into said main flow of gas (44);
at least one of an annular brush seal (28) and an annular labyrinth seal
(56) disposed between said stator (24) and rotor (26) and across said path of secondary flow of gas (48) such that said at least one seal (28, 56) blocks at least a portion of said secondary flow of gas (48);
a first gas-flow deflector (30) formed by an edge (24a) of said stator (24) adjacent to said root (40) of said downstream one of said stages (38) of said rotor
(26); and a second gas-flow deflector (32) formed by an edge (40a) of said root (40) of said downstream one of said stages (38) of said rotor (26) such that said first gas-flow deflector (30) is located spaced from and above said second gas-flow deflector (32) so that said secondary flow of gas (48) from said wheel space cavity (46) into said main flow of gas (44) turns between said first and second gas-flow deflectors (30, 32) toward said downstream one of said stages (38) of said rotor (26) and into said main flow of gas (44) in a tangential relationship to said main flow of gas (44) and to said root (26) of said downstream one of said stages (38) of said rotor (26).
2. The subassembly (22) of claim 1 further comprising:
at least said root (40) of said downstream one of said stages (38) of said rotor (26) defining a steam bypass passageway (54) therethrough open to said wheel space cavity (46) for diverting at least a portion of said secondary flow of gas (48) from passing into said main flow of gas (44).
3. The subassembly (22) of claim 2 in which said steam bypass passageway (54) has a size adapted for diverting at least a portion of said secondary flow of gas (48) from passing into said main flow of gas (44).
4. The subassembly (22) of claim 1 in which said brush seal (28) has an attached end (28a) and a free end (28b), said attached end (28a) of said brush seal (28) being mounted to said stator (24) and said free end (28b) of said brush seal (28) extending into said wheel space cavity (46) toward said rotor (24).
5. The subassembly of claim 1 in which said annular labyrinth seal (56) is aligned with said stator (24) and rotor (26) and is formed on at least one of said stator (24) and rotor (26) and extends into said wheel space cavity (46) between said stator (24) and rotor (26), said labyrinth seal (56) for blocking at least a portion of said secondary flow of gas (48).
6. A method of enhancing the performance of a steam-type gas turbine, said method comprising the steps of: providing a stator (24) having a longitudinally extending axis (34);
providing a rotor (26) coaxially aligned with and disposed radially adjacent to and apart from the stator (24) wherein the rotor (26) includes at least a pair of stages (36, 38) interconnected to one another and located respectively upstream and downstream relative to one another with each of said stages (36, 38) having in an annular arrangement a plurality of roots (40) and blades (42) mounted to said roots (40);
introducing a main flow of gas (44) moving in a path spaced radially outward from and along the longitudinally extending axis (34) of the stator (24) and rotor (26) and in one direction between the blades (42) of the adjacent upstream and downstream stages (36, 38) of the rotor (26);
forming at least one wheel space cavity (46) between the stator (24) and the upstream and downstream stages (36, 38) of the rotor (26) having opposite upstream and downstream ends (46a, 46b) open to the main flow of gas (44) at the respective upstream and downstream stages (36, 38) of the rotor (26);
introducing at least one secondary flow of gas (48) moving in another path through the wheel space cavity (46) between the upstream and downstream stages (36, 38) of the rotor (26) from the upstream end (46a) to the downstream end (46b) of the wheel space cavity (46) and into the main flow of gas (44);
providing at least one of an annular brush seal (28) and an annular labyrinth seal disposed between the stator (24) and rotor (26) and across the path of secondary flow of gas (48) such that said at least one seal (28, 56) blocks at least a portion of the secondary flow of gas (48);
modifying an edge (24a) of the stator (24) adjacent to the root (40) of the downstream one of the stages (38) of the rotor (26) into a first gas-flow deflector
(30); and modifying an edge (40a) of the root (40) of the downstream one of the stages (38) of the rotor (26) into a second gas-flow deflector (32) such that first gas- flow deflector (30) is located spaced from and above the second gas-flow deflector (32) so that the secondary flow of gas (48) from the wheel space cavity (46) into the main flow of gas (44) turns between the first and second gas-flow deflectors (30, 32) toward the downstream one of the stages (38) of the rotor (26) and into the main flow of gas (44) in a tangential relationship to the main flow of gas (44) and to the root (40) of the downstream one of the stages (38) of the rotor (26).
7. The method of claim 6 further comprising the step of:
forming a steam bypass passageway (54) through at least the root (40) of the downstream one of the stages (38) of the rotor (26) open to the wheel space cavity (46) for diverting at least a portion of the secondary flow of gas (48) from passing into the main flow of gas (44).
8. The method of claim 7 in which the steam bypass passageway forming step includes forming the steam bypass passageway (54) at a size adapted to divert at least a portion of the secondary flow of gas (48) from passing into the main flow of gas (44).
9. The method of claim 6 in which the brush seal (28) has an attached end (28a) and a free end (28b), the attached end (28a) of the brush seal (28) being mounted to the stator (24) and the free end (28b) of the brush seal (28) extending into the wheel space cavity (46) toward the rotor (26).
10. The method of claim 6 in which said annular labyrinth seal (56) aligned with the stator (24) and the rotor (26) and being formed on at least one of the stator (24) and the rotor (26) and extending into the wheel space cavity (46) between the stator (24) and the rotor (26), the labyrinth seal (56) for blocking at least a portion of the secondary flow of gas (48).
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002529645A JP2004510089A (en) | 2000-09-20 | 2001-08-17 | Steam-type gas turbine subassembly and method for enhancing turbine performance |
| KR1020027006341A KR20020045618A (en) | 2000-09-20 | 2001-08-17 | Steam-type gas turbine subassembly and method for enhancing turbine performance |
| AU2001285074A AU2001285074A1 (en) | 2000-09-20 | 2001-08-17 | Steam-type gas turbine subassembly and method for enhancing turbine performance |
| DE10194332T DE10194332T1 (en) | 2000-09-20 | 2001-08-17 | Steam turbine gas turbine subassembly and method for improving turbine performance |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US66546500A | 2000-09-20 | 2000-09-20 | |
| US09/665,465 | 2000-09-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2002025066A1 true WO2002025066A1 (en) | 2002-03-28 |
Family
ID=24670210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US2001/025915 WO2002025066A1 (en) | 2000-09-20 | 2001-08-17 | Steam-type gas turbine subassembly and method for enhancing turbine performance |
Country Status (8)
| Country | Link |
|---|---|
| JP (1) | JP2004510089A (en) |
| KR (1) | KR20020045618A (en) |
| CN (1) | CN1392917A (en) |
| AU (1) | AU2001285074A1 (en) |
| CZ (1) | CZ20021732A3 (en) |
| DE (1) | DE10194332T1 (en) |
| RU (1) | RU2002113105A (en) |
| WO (1) | WO2002025066A1 (en) |
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| WO2009106045A1 (en) * | 2008-02-28 | 2009-09-03 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
| EP2778351A1 (en) * | 2013-03-13 | 2014-09-17 | Kabushiki Kaisha Toshiba | Steam turbine |
| GB2533221A (en) * | 2014-12-11 | 2016-06-15 | Snecma | Impeller having a radial seal for a turbine engine turbine |
| GB2533223A (en) * | 2014-12-11 | 2016-06-15 | Snecma | Impeller having spoilers for a turbine engine turbine |
| DE112017001541B4 (en) | 2016-03-25 | 2022-05-19 | Mitsubishi Power, Ltd. | ROTARY MACHINE |
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| US7549834B2 (en) * | 2006-06-19 | 2009-06-23 | General Electric Company | Actuation pressure control for adjustable seals in turbomachinery |
| CA2738797C (en) * | 2008-09-29 | 2014-04-22 | Andrew L. Bender | High efficiency turbine |
| JP5591042B2 (en) | 2010-09-17 | 2014-09-17 | 三菱重工業株式会社 | Turbine |
| CN103541776B (en) * | 2013-10-15 | 2015-12-30 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Axial seal structure between a kind of gas turbine wheel disk |
| CN104329125B (en) * | 2014-09-04 | 2016-08-31 | 中国南方航空工业(集团)有限公司 | Gas turbine |
| CN104632413B (en) * | 2015-01-30 | 2018-05-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine combustion cylinder pressure turns static seal structure |
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| US3291447A (en) * | 1965-02-15 | 1966-12-13 | Gen Electric | Steam turbine rotor cooling |
| US5613829A (en) | 1996-05-03 | 1997-03-25 | General Electric Company | Gas turbine subassembly having a brush seal |
| US5749584A (en) * | 1992-11-19 | 1998-05-12 | General Electric Company | Combined brush seal and labyrinth seal segment for rotary machines |
| EP0953730A2 (en) * | 1998-04-28 | 1999-11-03 | General Electric Company | Repairing method for dovetail grooves |
-
2001
- 2001-08-17 CZ CZ20021732A patent/CZ20021732A3/en unknown
- 2001-08-17 KR KR1020027006341A patent/KR20020045618A/en not_active Application Discontinuation
- 2001-08-17 WO PCT/US2001/025915 patent/WO2002025066A1/en active Application Filing
- 2001-08-17 DE DE10194332T patent/DE10194332T1/en not_active Withdrawn
- 2001-08-17 RU RU2002113105/06A patent/RU2002113105A/en not_active Application Discontinuation
- 2001-08-17 CN CN01802784A patent/CN1392917A/en active Pending
- 2001-08-17 AU AU2001285074A patent/AU2001285074A1/en not_active Abandoned
- 2001-08-17 JP JP2002529645A patent/JP2004510089A/en not_active Withdrawn
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3291447A (en) * | 1965-02-15 | 1966-12-13 | Gen Electric | Steam turbine rotor cooling |
| US5749584A (en) * | 1992-11-19 | 1998-05-12 | General Electric Company | Combined brush seal and labyrinth seal segment for rotary machines |
| US5613829A (en) | 1996-05-03 | 1997-03-25 | General Electric Company | Gas turbine subassembly having a brush seal |
| EP0953730A2 (en) * | 1998-04-28 | 1999-11-03 | General Electric Company | Repairing method for dovetail grooves |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100383364C (en) * | 2002-10-31 | 2008-04-23 | 通用电气公司 | Flow passage sealing of turbine and streamline structure thereof |
| DE10350626B4 (en) * | 2002-10-31 | 2014-12-11 | General Electric Co. | Ripple seal and streamline configuration for a turbine |
| WO2009106045A1 (en) * | 2008-02-28 | 2009-09-03 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
| US8753070B2 (en) | 2008-02-28 | 2014-06-17 | Mtu Aero Engines Gmbh | Device and method for redirecting a leakage current |
| EP2778351A1 (en) * | 2013-03-13 | 2014-09-17 | Kabushiki Kaisha Toshiba | Steam turbine |
| JP2014177869A (en) * | 2013-03-13 | 2014-09-25 | Toshiba Corp | Steam turbine |
| US10018046B2 (en) | 2013-03-13 | 2018-07-10 | Kabushiki Kaisha Toshiba | Steam turbine |
| GB2533221A (en) * | 2014-12-11 | 2016-06-15 | Snecma | Impeller having a radial seal for a turbine engine turbine |
| GB2533223A (en) * | 2014-12-11 | 2016-06-15 | Snecma | Impeller having spoilers for a turbine engine turbine |
| GB2533221B (en) * | 2014-12-11 | 2021-05-12 | Snecma | Impeller having a radial seal for a turbine engine turbine |
| GB2533223B (en) * | 2014-12-11 | 2021-06-09 | Snecma | Impeller having spoilers for a turbine engine turbine |
| DE112017001541B4 (en) | 2016-03-25 | 2022-05-19 | Mitsubishi Power, Ltd. | ROTARY MACHINE |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20020045618A (en) | 2002-06-19 |
| CN1392917A (en) | 2003-01-22 |
| AU2001285074A1 (en) | 2002-04-02 |
| DE10194332T1 (en) | 2003-08-21 |
| RU2002113105A (en) | 2003-11-27 |
| JP2004510089A (en) | 2004-04-02 |
| CZ20021732A3 (en) | 2002-10-16 |
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