US20060064988A1 - Turbine power plant having minimal-contact brush seal augmented labyrinth seal - Google Patents
Turbine power plant having minimal-contact brush seal augmented labyrinth seal Download PDFInfo
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- US20060064988A1 US20060064988A1 US11/034,563 US3456305A US2006064988A1 US 20060064988 A1 US20060064988 A1 US 20060064988A1 US 3456305 A US3456305 A US 3456305A US 2006064988 A1 US2006064988 A1 US 2006064988A1
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- 238000001816 cooling Methods 0.000 claims abstract description 31
- 239000012530 fluid Substances 0.000 claims abstract description 18
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- 239000007789 gas Substances 0.000 claims description 9
- 230000000717 retained effect Effects 0.000 claims description 8
- 239000000567 combustion gas Substances 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000004323 axial length Effects 0.000 claims 2
- 238000007789 sealing Methods 0.000 claims 2
- 230000002401 inhibitory effect Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
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- 229910001092 metal group alloy Inorganic materials 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/002—Sealings comprising at least two sealings in succession
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- 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
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/324—Arrangements for lubrication or cooling of the sealing itself
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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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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A stationary gas turbine engine includes an axial compressor; a turbine; a stationary inner barrel downstream of the compressor; a brush seal including a ring-shaped holder supported by the inner barrel, and a multiplicity of inwardly extending bristle members having an ambient temperature clearance of not less than 0.015 percent of a rotor land region diameter of the rotor under cold conditions for restricting air passage into the chamber from the compressor. The flow of cooling air from the chamber is preferably alterable by a fluid port extending through one wall of the inner barrel, the fluid port being connected to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber. A calibrated needle valve can adjustably restrict the flow of auxiliary air for controlling a monitored operating parameter such as the temperature within the chamber. The engine can have an outer barrel surrounding the inner barrel, air flowing therebetween toward the combustor, and including a radial fluid port, and a fluid conduit connected between the passage and the fluid port, the auxiliary source being connected to the fluid port external of the outer barrel. A method for controlling cooling air flow in the power plant includes providing the brush seal; connecting the brush seal in augmenting relation to the labyrinth seal; and spacing the bristles from the land region of the rotor.
Description
- The present invention relates to turbine power plants and more particularly to large, stationary turbine power generators of the type used for utility services.
- A typical stationary turbine power plant, known as Model Series 7001 simple cycle, single shaft, heavy duty gas turbine (Frame-7 machine), is available from General Electric of Schenectady, N.Y. In this and similar gas turbines, a seal is located between an axial compressor rotor and a stationary inner barrel member, a chamber within the inner barrel member being supplied with cooling air from the last stage of the compressor by a controlled amount of leakage through the seal. The cooling air is then utilized for cooling of a first turbine stage of the machine. A set of rotor bearings is located in the cavity.
- Leakage in excess if a predetermined amount that is required for cooling of the turbine becomes parasitic and contributes to inefficiency of the machine. This is a serious problem in turbine power plants of the prior art, in that the labyrinth seals degrade in operation because of thermal expansions and other factors that cause knife-edge members and adjacent rotating elements of the seals to be worn away quickly, particularly during shut-down sequences. This is caused, for example, by shrinkage of the inner barrel member being more rapid than shrinkage of the rotor at the seal to the rotor being more massive. Thus in the frame-7 machines, the bypass air flow increases to approximately 100,000 lb/hr from the 30,000 lb/hr that is considered optimal. Consequently, there is a loss of power that is believed to be between 1.5 MW and 3.0 MW.
- Brush seals for gas-turbine engines are known, being disclosed, for example in “Brush Seals” Directions, September 1993 . As disclosed therein, a brush seal consists of densely packed metallic bristles that are welded between a down-stream backing plate and an up-stream side plate. In a typical round seal for aircraft turbine applications, the plates are ring-shaped, the bristles extending radially inwardly at a trailing lay angle and making an interference contact with a rotor element, so that the bristles become curved and follow the rotor as it grows and shrinks during engine operation.
- Brush seals have not been applied to existing large power plant turbines for a number of reasons. For example, the existing rotor components, being made from elements of low carbon steel alloys that are selected for certain thermal expansion properties, are believed to be unsuitable as wear surfaces for contact by the bristles, particularly during the extended operation cycles that are demanded of stationary power plants. Suitable hardening of applicable compressor rotor members is believed to be prohibitively expensive, particularly in existing equipment.
- Thus there is a need for an improved rotor seal for large stationary plants, that overcomes the disadvantages of the prior art.
- The present invention meets this need by providing a turbine power plant with a combination brush and labyrinth compressor seal wherein the brush seal operates in a non-contact mode following start-up. In one aspect of the invention, a stationary gas turbine engine for the power plant includes a multistage axial compressor that has a rotor having a cylindrical land region downstream of a last-stage of the compressor, the land region having an outside diameter D; a turbine shaft-coupled to the rotor of the compressor; a combustor fluid-coupled between the compressor and the turbine; a stationary inner barrel downstream of the compressor, air flowing from the compressor to the combustor passing outside of the inner barrel, a chamber within the inner barrel forming a passage for cooling air from the compressor, the cooling air flowing from the chamber and being mixed with combustion gases upstream of the turbine; a brush seal for restricting air passage into the chamber from the compressor, the brush seal including a ring-shaped holder; a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder; and means for fastening the holder to the inner barrel, wherein, when the power plant is inactive, the bristles have an ambient temperature clearance of not less than 0.015 percent of the diameter D from the land region of the rotor.
- The engine can further include means for selectively altering the flow of cooling air from the chamber, including a passage extending through one wall of the inner barrel; means for connecting the fluid port to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber; and means for changeably restricting flow of pressure air into the chamber from the auxiliary source of pressure air. The compressor can provide at least a portion of the auxiliary source of pressure air. The means for changeably restricting can include means for removably mounting a device being a plug or a jet in the passage.
- Preferably the means for selectively altering the flow of cooling air also includes a valve for adjustably restricting flow of pressure air into the chamber from the auxiliary source of pressure air; and means for monitoring an operating parameter of the engine, the operating parameter being responsive to the flow of cooling air from the chamber. The valve is preferably a calibrated needle valve for facilitating repeatable control of the cooling flow. The means for monitoring can include a temperature sensor for indicating temperatures within the chamber. The engine can also have an outer barrel surrounding the inner barrel and including a fluid port extending radially through one wall thereof, the gas flow from the compressor to the combustor passing between the outer barrel and the inner barrel, the means for connecting the passage including a fluid conduit connected between the passage and the fluid port, and means for connecting the auxiliary source of pressure air to the fluid port external of the outer barrel.
- The engine can further include an insert ring connecting segments of the inner barrel, the insert ring being located proximate the land region of the rotor, the means for fastening the brush seal to the inner barrel including the holder being fastened to the insert ring by a plurality of threaded fasteners. Preferably the brush seal, including the holder thereof, is segmented for facilitating assembly with the insert ring.
- In another aspect of the invention, a turbine power plant improvement includes a brush seal connected to a stationary barrel member between an axial compressor outlet and a cavity within the barrel member for augmenting a labyrinth seal that limits the flow of cooling air into the cavity, the brush seal having a ring-shaped holder, a multiplicity of bristle members being rigidly anchored to the holder and extending radially inwardly therefrom toward a rotor land region, wherein the bristles have an ambient temperature clearance of not less than 0.015 percent of a diameter D of the land region when the power plant is inactive.
- In a further aspect of the invention, a method for controlling cooling air flow in a turbine power plant having a multistage axial compressor, a turbine shaft-coupled to a rotor of the compressor, a combustor fluid coupled between the compressor and the turbine, and a labyrinth seal between the rotor and a stationary inner barrel member, the rotor having a cylindrical land region of diameter D, includes the steps of:
- (a) providing a brush seal having a ring-shaped holder, a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder;
- (b) connecting the brush seal in augmenting relation to the labyrinth seal; and
- (c) spacing the bristle members from the land region of the rotor by an ambient temperature clearance of not less than 0.015 percent of the diameter D when the power plant is inactive.
- The power plant can include an insert ring fastened to the inner barrel in axially spaced relation to a portion of the rotor member, the method including the further steps of:
- (a) removing the insert ring from the inner barrel member;
- (b) providing an adapter ring;
- (c) mounting the brush seal to the adapter ring; and
- (d) fastening the adapter ring to the inner barrel member in place of the insert ring.
- The step of providing the adapter ring can include the step of modifying the insert ring. The method can include the further steps of:
- (a) providing an auxiliary source of pressure air;
- (b) fluid-connecting the auxiliary source to an interior cavity portion of the inner barrel member for augmenting the flow of cooling air;
- (c) connecting an adjustable valve between the auxiliary source and the inner barrel member for variably restricting air flow from the auxiliary source and the inner barrel member;
- (d) monitoring an operating parameter of the power plant; and
- (e) adjusting the adjustable valve in response to changes in the operating parameter.
- These and other features, aspects, and advantages of the present invention will become better understood with reference to the following description, appended claims, and accompanying drawings, where:
-
FIG. 1 is a fragmentary sectional elevational view of a prior art stationary turbine power plant machine; -
FIG. 2 is a detail sectional view of the prior art machine ofFIG. 1 within region 2 thereof; -
FIG. 3 is a graph showing start-up and shut-down compressor discharge pressure and temperature profiles of the prior art machine ofFIG. 1 ; -
FIG. 4 is a sectional view as inFIG. 2 , showing the machine as improved according to the present invention; and -
FIG. 5 is a lateral sectional diagrammic view of the machine ofFIG. 4 . - The present invention is directed to a turbine power plant having improved control of cooling bypass air. With reference to
FIGS. 1-3 of the drawings, a prior artgas turbine machine 10 has a multi-stageaxial compressor 12, acombustor 14, and a turbine 16 that is shaft-coupled to thecompressor 12 within aninner barrel member 18, a set of rotor bearings also being mounted within abearing housing 20 that is located within thebarrel member 18. Thecompressor 12 has a last orseventeenth stage 17R on arotor member 24, and an associated stator 17S that supportively contacts theinner barrel member 18. Alabyrinth seal 22 is located between therotor member 24 and thebarrel member 18, theseal 22 including a plurality of stationary knife-edge members 26 projecting inwardly from thebarrel member 18 toward a series of radially offset cylindrical portions of therotor member 18. A small annular clearance normally exists between each knife-edge member 26 and therotor member 18 as indicated by a radial gap distance LD, the distance LD being made approximately 0.030 inch at manufacture. Achamber 28 is formed within thebarrel member 18, being supplied with cooling air from the last stage of thecompressor 12 by a controlled amount of leakage through thelabyrinth seal 22. The cooling air, after passing therotor bearing housing 20, flows outwardly in front of afirst wheel 30 of the turbine 16 and mixes with high-temperature gases passing from thecombustor 14 through anozzle block 31. Thebarrel member 18 can be segmented, being maintained in alignment by an interlockinginsert ring 32 that also supports a final stator member 34 of thecompressor 12. Typically, theinner barrel member 18 is formed by a pair of semi-circular segments, theinsert ring 32 also being formed in three segments that overlap joints between the segments of the barrel member. Theinsert ring 32 is axially spaced from a portion of therotor member 24 by a distance C through which the cooling air flows toward thelabyrinth seal 22, the distance C corresponding to a space between therotor 17R and the stator 17S, the stator 17S also having a width W. Themachine 10 under design conditions produces air flow at a pressure of approximately 167 psi gage and a temperature of approximately 675° F. at the exit of thecompressor 12, the main portion of the flow being between theinner barrel member 18 and anouter barrel member 36 that surrounds theinner barrel member 18. A radially spaced pair of “angel wings” 34 project forwardly toward thecompressor 12 from thefirst wheel 30 for limiting cooling air flow from thechamber 28 to the turbine 16. Thechamber 28 within theinner barrel member 18 is intended to be maintained at a pressure of proximately 82 psi gage by the flow of cooling air through thelabyrinth seal 22. - The
turbine machine 10, being of the type that is commercially available asSeries 7001 heavy duty gas turbine from the previously identified General Electric Corp., has a somewhat protracted start-up sequence that lasts over one hour and a shut-down sequence that lasts approximately one hour as characterized inFIG. 3 by associated discharge pressures and temperatures of thecompressor 12.FIG. 3 also includes power loading in megawatts and rotational speed as a percentage of rated speed for the start-up and shut-down sequences, plotted against time. Typically, there is significant wear of theknife edge members 26 against therotor member 24 during portions of the shut-down sequence from the as manufactured condition, the distance LD rapidly increasing to between approximately 0.070 inch and approximately 0.110 inch. This increased clearance adversely affects performance of themachine 10 by lowering the flow of pressurized air into thecombustor 14 as well as excessively lowering the turbine inlet temperature (by mixing the low temperature stream of compressed cooling air with the stream of hot combustion gases from the combustor 14). - According to the present invention, and with further reference to
FIGS. 4 and 5 , the machine, designated 10′, is provided with abrush seal 40 for augmenting thelabyrinth seal 22. Thebrush seal 40 includes abacking plate 42, a multiplicity of tightly packed bristlemembers 44, and acover plate 46. Thebristle members 44 are clamped between thebacking plate 42 and thecover plate 46, outer extremities of the bristle members being positively anchored to theplates bristle members 44 are typically very thin, being formed of a high-strength metal alloy, and closely packed at a density of approximately - 4,500 per square inch.
- In an exemplary configuration of the
machine 10′, aretainer plate 48 holds thebrush seal 40 in fixed relation to thebarrel member 18 by interlocking engagement with a counterpart of the insert ring, designatedadapter ring 32′, thebacking plate 42 having a generally L-shaped cross-section, one leg of which axially projects into theadapter ring 32′. Theretainer plate 48 is fastened to theinsert ring 32′by a plurality of threadedfasteners 50. In the exemplary configuration ofFIG. 4 , thefasteners 50 are conventional undercut flat head machine screws having a thread diameter of approximately 0.099 inch, being spaced circumferentially not more than 6 inches on center, and staked in place. As further shown inFIG. 4 , thebristle members 44 are located in spaced relation to aland region 52 of therotor member 24, the land region having a diameter D, thebristle members 44 being radially spaced at a distance BD from theland region 52. Thus thebrush seal 40 is fluid-connected in series with the labyrinth seal In a “cold” condition of themachine 10′, the distance BD is preferably approximately 0.010 inch for preventing unwanted contact between thebristle members 44 and therotor member 24. It is contemplated that momentary contact between thebristle members 44 and therotor member 24 may occur during the shut-down sequence as explained above, but that no such contact will occur either during the initial portion of the start-up sequence or during steady-state full load operation of themachine 10′. It is believed that the preferred avoidance of continuous brush contact is attained when the “cold” clearance (with therotor member 18 stationary) is not less than 0.015 percent of the diameter D. In the case of the “Frame-7 machine”, the diameter D is approximately 50.5 inches; accordingly, the distance BD is preferably not less than 0.00757 inch, being more preferably approximately 0.010 inch. In the “cold” condition, thebacking plate 42 is radially spaced at a distance BB from therotor member 24, the distance BB being sufficiently great for preventing contact with the rotor member, yet sufficiently small for supporting thebristle members 44 against upstream air pressure. In the above example, a preferred value for the distance BB is approximately 0.170 inch. Thebacking plate 42 is also tapered inwardly and forwardly for fail-safe limitation of rotor contact in the event of abnormal operating conditions. Under design conditions, the clearance distance BD is contemplated to be somewhat less than in the cold condition in which themachine 10′ is characterized, but not so much less as to create contact. If testing shows otherwise, the clearance distance BD is preferably to be made slightly larger. - It is contemplated that the
brush seal 40 be added to existingturbine machines 10 having worn labyrinth seals 22 as described above. In the present invention this facilitated by the need for modification of theinsert ring 32 only. Particularly, theadapter ring 32′ can be formed by axially shortening the existinginsert ring 32, forming an annular channel as indicated at 54, and forming threadedopenings 56 for thefasteners 50. Theadapter ring 32′ can be segmented as described above in connection with theinsert ring 32. - It is also contemplated that the
brush seal 40 be used in “fresh” installations having no wear of thelabyrinth seal 22. In such cases, the labyrinth seal radial spacing LD, which is only 0.03 inch, quickly increases as a result of wear during shut-down as described above. Nevettheless, it may be desired to augment the flow of cooling air into thechamber 28. Accordingly, and as shown inFIG. 4 , thebarrel member 18 is preferably provided with one or more threadedpassages 60. Selected ones of thepassages 60 are closed or partially blocked byrespective plugs 62 and/orjets 64. - Also, some or all of the
passages 60 can be fluid-connected to an auxiliary source 66 of pressure air as shown InFIG. 5 . More particularly, theouter barrel member 36 of theturbine machine 10 is provided with one or morefluid ports 70, aninner conduit 72 being fluid-connected between eachport 70 and a corresponding one of the threadedpassages 60, anouter conduit 74 being fluid-connected between the port(s) 70 and the auxiliary source 66 and having an adjustable valve 76 series-connected therein for adjustably restricting the flow of auxiliary cooling air into thechamber 28 of the inner barrel member. Preferably the valve 76 is a calibrated needle valve for facilitating repeatable adjustment thereof in response to a monitored operating parameter of themachine 10. The monitored operating parameter can be an inside temperature of theinner barrel member 18, which grows to exceed a preferred value if thebrush seal 40 is excessively effective in restricting the flow of cooling air from thecompressor 12 into thechamber 28.FIG. 5 shows athermocouple temperature sensor 78 that is normally provided with themachine 10 ofFIGS. 1-3 , thesensor 78 having aconventional indicator 80 associated therewith. Manual control of the needle valve 76 in response to readings of the indicator is appropriate in that the start-up sequence ofFIG. 3 is sufficiently slow. The auxiliary source 66 must be maintained at greater pressure than that of thechamber 28 for assuring the proper direction of flow. It will be understood that at least a portion of the auxiliary source 66 can be provided by thecompressor 12. Indeed, when any of thepassages 60 are left open or provided withjets 64, but not the inner andouter conduits compressor 12. Also, it may be preferred to take from an earlier stage of thecompressor 12, or from an independent source, to provide the auxiliary source 66 for reasons of greater efficiency and/or reduced cost. - The
turbine machine 10′ of the present invention provides improved control of cooling air into thechamber 28 for significantly increased output and efficiency in typical large power plant installations. Under conditions presently encountered, it is believed that the present invention will provide approximately 1.5 megawatts of additional power output from a typical installation of the Frame-7 machine, resulting in a savings on the order of $250,000 per machine, the installation cost being on the order of $30,000. - Although the present invention has been described in considerable detail with reference to certain preferred versions thereof, other versions are possible. Therefore, the spirit and scope of the appended claims should not necessarily be limited to the description of the preferred versions contained herein.
Claims (29)
1. A stationary gas turbine engine for a power plant, comprising:
(a) a multistage axial compressor, the compressor having a rotor, the rotor having a cylindrical land region downstream of a last-stage of the compressor, the land region having an outside diameter D;
(b) a turbine shaft-coupled to the rotor of the compressor;
(c) a combustor fluid coupled between the compressor and the turbine;
(d) a stationary inner barrel member downstream of the compressor, air flowing from the compressor to the combustor passing outside of the inner barrel member, a chamber within the inner barrel member forming a passage for cooling air from the compressor, the cooling air flowing from the chamber and being mixed with combustion gases upstream of the turbine; and,
(e) a brush seal for restricting air passage into the chamber from the compressor, the brush seal comprising:.
(i) a ring-shaped holder;
(ii) a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder; and
(iii) means for fastening the holder to the inner barrel member.
2. (canceled)
3. (canceled)
4. (canceled)
5. (canceled)
6. (canceled)
7. (canceled)
8. (canceled)
9. The engine of claim 1 , further comprising an insert ring connecting segments of the inner barrel member, the insert ring being located proximate the land region of the rotor, wherein the means for fastening the brush seal to the inner barrel member comprises the holder being fastened to the insert ring by a plurality of the threaded fasteners.
10. The engine of claim 9 , wherein the brush seal, including the holder thereof is segmented for facilitating assembly with the insert ring.
11. In a turbine power plant having a multistage axial compressor, a turbine shaft-coupled to a rotor of the compressor, a combustor fluid-coupled between the compressor and the turbine, and a labyrinth seal between the rotor and a stationary inner barrel member, the rotor having a cylindrical land region of diameter D, the improvement comprising a brush seal connected to the inner barrel and augmenting the labyrinth seal, being fluid connected in series therewith, the brush seal comprising:
(a) a ring-shaped holder;
(b) a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder; and
(c) means for fastening the holder to the inner barrel member.
12. (canceled)
13. (canceled)
14. (canceled)
15. (canceled)
16. (canceled)
17. A method for controlling cooling air flow in a turbine power plant having a multistage axial compressor, a turbine shaft-coupled to a rotor of the compressor, a combustor fluid coupled between the compressor and the turbine, and a labyrinth seal between the rotor and a stationary inner barrel member, the rotor having a cylindrical land region of diameter D, comprising the steps of:
(a) providing a brush seal having a ring-shaped holder, a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder;
(b) connecting the brush seal in augmenting relation to the labyrinth seal; and
(c) spacing the bristle members from the land region of the rotor.
18. The method of claim 17 , wherein the power plant includes an insert ring fastened to the inner barrel member in axially spaced relation to a portion of the rotor member, the method comprising the further steps of:
(a) removing the insert ring from the inner barrel member;
(b) providing an adapter ring;
(c) mounting the brush seal to the adapter ring; and
(d) fastening the adapter ring to the inner barrel member in place of the insert ring.
19. The method of claim 18 , wherein the step of providing the adapter ring comprises the step of modifying the insert ring.
20. (canceled)
21. A refurbished gas turbine engine component having at least one knife edge seal for inhibiting air leakage through an intercomponent gap between the component and a second component, the refurbished component characterized by:
a) a brush seal mounted on the refurbished component in tandem with the knife edge seal, the bristles of the brush seal extending toward the second component for impeding the leakage of air through the intercomponent gap.
22. The refurbished component of claim 1 characterized in that the component comprises two component segments, the brush seal is also segmented and the brush seal segments are mounted in a circumferentially extending groove so that the seal is installable and removable by separating the component segments and sliding the brush seal segments circumferentially in the groove.
23. A method of improving the air sealing effectiveness between a rotating component and a nonrotating component in a turbine engine, the rotating and nonrotating components being separated by a gap with knife edge seals extending across the gap to inhibit leakage of air therethrough, the method characterized by:
a) providing a brush seal;
b) reconfiguring the nonrotating component to provide means for receiving and retaining the brush seal in tandem with the knife edge seals; and
c) installing the brush seal so that the seal bristles extend toward the rotating component to impede the flow of air through the gap the brush seal being retained by the receiving and retaining means.
24. The method of claim 3 wherein the nonrotating component is hollow and substantially cylindrical and has a wall thickness and a face, the method characterized in that the step of reconfiguring the nonrotating component includes:
a) creating a capture slot in the face of the nonrotating component for radially retaining the brush seal; and
b) attaching a retainer to the nonrotating component so that the retainer cooperates with the face to axially trap the brush seal.
25. The method of claim 4 characterized in that the reconfiguring step includes reducing the wall thickness by a predefined amount in the vicinity of the face to form a seal seat and accommodate the radial dimension of the brush seal.
26. The method of claim 4 characterized in that the reconfiguring step regulates the axial length of the nonrotating component.
27. The method of claim 3 wherein the brush seal is a multilayered brush seal.
28. The method of claim 3 wherein the nonrotating component comprises upper and lower component segments each component segment subtending approximately 180 degrees of arc, the retainer also comprises upper and lower retainer segments, each retainer segment subtending approximately 180 degrees of arc, and the brush seal comprises an upper brush seal segment subtending approximately 180 degrees of arc and one or more lower brush seal segments, the lower brush seal segments collectively subtending approximately 180 degrees of arc.
29. A method of improving the air sealing effectiveness between a rotating component and a nonrotating component in a turbine engine, the nonrotating component being hollow and substantially cylindrical and having a wall thickness and a face, the rotating and nonrotating components being separated by a gap with knife edge seals extending across the gap to inhibit leakage of air therethrough, the method characterized by:
a) reconfiguring the nonrotating component by reducing its axial length by a predetermined amount and reducing its wall thickness in the vicinity of the face by a predefined amount whereby a seal seat is formed;
b) creating an axially and circumferentially extending capture slot in the face of the nonrotating component;
c) attaching a retainer to the face so that the retainer cooperates with the face and the seal seat to define a circumferentially extending groove;
d ) installing a brush seal in the groove so that the bristles of the seal extend toward the rotating component to impede the flow of air through the gap; and,
e) the brush seal being radially retained by the capture slot and the seal seat and axially retained by the retaining ring and the face.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/034,563 US20060064988A1 (en) | 1996-05-31 | 2005-01-13 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
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US65656496A | 1996-05-31 | 1996-05-31 | |
US08/892,738 US5961279A (en) | 1996-05-31 | 1997-07-15 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
US09/288,943 US7059827B1 (en) | 1996-05-31 | 1999-04-09 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
US11/034,563 US20060064988A1 (en) | 1996-05-31 | 2005-01-13 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US09/288,943 Continuation US7059827B1 (en) | 1996-05-31 | 1999-04-09 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
Publications (1)
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US20060064988A1 true US20060064988A1 (en) | 2006-03-30 |
Family
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US09/288,943 Expired - Fee Related US7059827B1 (en) | 1996-05-31 | 1999-04-09 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
US11/034,563 Abandoned US20060064988A1 (en) | 1996-05-31 | 2005-01-13 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
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Application Number | Title | Priority Date | Filing Date |
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US09/288,943 Expired - Fee Related US7059827B1 (en) | 1996-05-31 | 1999-04-09 | Turbine power plant having minimal-contact brush seal augmented labyrinth seal |
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US (2) | US7059827B1 (en) |
Cited By (5)
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US9217336B2 (en) | 2012-02-16 | 2015-12-22 | Solar Turbines Incorporated | Gas turbine engine lubrication fluid barrier |
CN106596702A (en) * | 2016-12-27 | 2017-04-26 | 西北大学 | Multi-position sample dissolution device |
US10832395B2 (en) * | 2019-03-25 | 2020-11-10 | Raytheon Technologies Corporation | Systems and methods for inspecting bristles using a digital camera |
US11125097B2 (en) * | 2018-06-28 | 2021-09-21 | MTU Aero Engines AG | Segmented ring for installation in a turbomachine |
US20220025776A1 (en) * | 2020-07-22 | 2022-01-27 | Raytheon Technologies Corporation | Seal runner flow damper |
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US7052015B2 (en) * | 2002-08-06 | 2006-05-30 | United Technologies Corporation | Cooling arrangement for brush seal |
DE10358876A1 (en) * | 2003-12-16 | 2005-07-28 | Fag Kugelfischer Ag | Gasket with contactless abutment rings |
US7383167B2 (en) * | 2004-01-29 | 2008-06-03 | General Electric Company | Methods and systems for modeling power plants |
ITMI20061086A1 (en) * | 2006-06-01 | 2007-12-02 | Nuovo Pignone Spa | DEVICE TO OPTIMIZE COOLING IN GAS TURBINES |
US8256575B2 (en) * | 2007-08-22 | 2012-09-04 | General Electric Company | Methods and systems for sealing rotating machines |
US8128348B2 (en) * | 2007-09-26 | 2012-03-06 | United Technologies Corporation | Segmented cooling air cavity for turbine component |
US8333551B2 (en) * | 2007-09-28 | 2012-12-18 | General Electric Company | Embedded fiber optic sensing device and method |
US8083236B2 (en) * | 2009-09-22 | 2011-12-27 | Hamilton Sundstrand Corporation | Staggered seal assembly |
US9587505B2 (en) | 2013-12-05 | 2017-03-07 | General Electric Company | L brush seal for turbomachinery application |
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US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
US5314598A (en) * | 1991-02-07 | 1994-05-24 | Rolls Royce Plc | Electrochemical broaching apparatus |
US5400952A (en) * | 1993-10-25 | 1995-03-28 | General Electric Company | Method and apparatus for damping a brush seal |
US5474305A (en) * | 1990-09-18 | 1995-12-12 | Cross Manufacturing Company (1938) Limited | Sealing device |
US5639095A (en) * | 1988-01-04 | 1997-06-17 | Twentieth Technology | Low-leakage and low-instability labyrinth seal |
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US5318309A (en) * | 1992-05-11 | 1994-06-07 | General Electric Company | Brush seal |
US5308088A (en) * | 1992-08-20 | 1994-05-03 | General Electric Company | Brush seal with flexible backing plate |
US5630590A (en) * | 1996-03-26 | 1997-05-20 | United Technologies Corporation | Method and apparatus for improving the airsealing effectiveness in a turbine engine |
-
1999
- 1999-04-09 US US09/288,943 patent/US7059827B1/en not_active Expired - Fee Related
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2005
- 2005-01-13 US US11/034,563 patent/US20060064988A1/en not_active Abandoned
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US5639095A (en) * | 1988-01-04 | 1997-06-17 | Twentieth Technology | Low-leakage and low-instability labyrinth seal |
US5474305A (en) * | 1990-09-18 | 1995-12-12 | Cross Manufacturing Company (1938) Limited | Sealing device |
US5314598A (en) * | 1991-02-07 | 1994-05-24 | Rolls Royce Plc | Electrochemical broaching apparatus |
US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
US5400952A (en) * | 1993-10-25 | 1995-03-28 | General Electric Company | Method and apparatus for damping a brush seal |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9217336B2 (en) | 2012-02-16 | 2015-12-22 | Solar Turbines Incorporated | Gas turbine engine lubrication fluid barrier |
CN106596702A (en) * | 2016-12-27 | 2017-04-26 | 西北大学 | Multi-position sample dissolution device |
US11125097B2 (en) * | 2018-06-28 | 2021-09-21 | MTU Aero Engines AG | Segmented ring for installation in a turbomachine |
US10832395B2 (en) * | 2019-03-25 | 2020-11-10 | Raytheon Technologies Corporation | Systems and methods for inspecting bristles using a digital camera |
US20220025776A1 (en) * | 2020-07-22 | 2022-01-27 | Raytheon Technologies Corporation | Seal runner flow damper |
US11371374B2 (en) * | 2020-07-22 | 2022-06-28 | Raytheon Technologies Corporation | Seal runner flow damper |
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