MXPA97003218A - Subassemble of gas turbine that has a seal of escobi - Google Patents
Subassemble of gas turbine that has a seal of escobiInfo
- Publication number
- MXPA97003218A MXPA97003218A MXPA/A/1997/003218A MX9703218A MXPA97003218A MX PA97003218 A MXPA97003218 A MX PA97003218A MX 9703218 A MX9703218 A MX 9703218A MX PA97003218 A MXPA97003218 A MX PA97003218A
- Authority
- MX
- Mexico
- Prior art keywords
- gas turbine
- circumferential portion
- rotor
- rotation
- state
- Prior art date
Links
- 238000011068 load Methods 0.000 claims abstract description 63
- 239000007789 gas Substances 0.000 description 127
- 238000002485 combustion reaction Methods 0.000 description 8
- 210000003027 Ear, Inner Anatomy 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 210000003660 Reticulum Anatomy 0.000 description 2
- 238000002372 labelling Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reaction Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Abstract
The present invention relates to a gas tubina subassembly comprising: a) a gas turbine stator having a longitudinally extending shaft generally, b) a gas turbine rotor having first condition generally stable and a second rotation / load condition and coaxially aligned generally with and radially disposed within and radially apart from the gas turbine stator, wherein the gas turbine rotor includes an outer surface with first and second circumferential portions that are they extend longitudinally and longitudinally, with the first circumferential portion having a first manofactured diameter which is generally constant over the longitudinal extension of the circumferential portion and with the second circumferential portion having a second manofacturate which is smaller in its entirety than the circumferential portion. first diameter on the longitudinal extension of the second portion circufer and, wherein the gas turbine rotor and the gas turbine stator together experience a predetermined longitudinal differential thermal radial movement when the rotor undergoes a transition from the first state of rotation / load to the second state of rotation / loading and c) a generally annular wiper seal generally coaxially aligned with the gas turbine stator, the wiper seal a joined end and a free end, with the attached end attached to the gas turbine stator and with the free end extending into the gas turbine stator, wherein the free end is positioned in general line-to-line contact with the first circumferential portion when the gas turbine rotor is in the first state of rotation / charge and, where, the movement radial diffferential and thermal longitudinal predetermined oncludes the free end that moves radially inward and longitudinally through the second circumference
Description
SUBASSAMBLE OF GAS TURBINE THAT HAS A SCRAP SEAL
Background of the Invention
The present invention relates generally to gas turbines and, more particularly to a gas turbine subassembly having a brush seal. Gas turbines include combustion type gas turbines, which use combustion gases to spin rotors and steam type gas turbines, which use steam to spin 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 flow relation, an air inlet (or inlet), a compressor, a combustion chamber, a turbine and a gas outlet (or exhaust nozzle). A steam type gas turbine has a gas path that typically includes a steam inlet, a turbine and a steam outlet. The compressors and turbines include rotation motors rotatably connected to non-rotating surrounding stators by suitable supports. The gas paths between the compressors and the combustion chambers and the turbines include annular transition ducts having radially internal and external stator portions. In certain axial locations, the rotors typically include rotor blades projecting radially outwardly and, in certain axial locations, stators that typically include stator blades that project radially inwardly. Some gas turbines include high and low pressure compressors and high and low pressure turbines with the high pressure compressor rotor surrounding the low pressure compressor rotor and the high pressure turbine rotor surrounding the low turbine rotor. Pressure. The leakage of gas between certain components of the gas turbine is undesirable because the gas is wasted (eg, air, combustion gas, steam, etc.) causing a loss in energy and efficiency. For example, such loss of energy and efficiency occurs due to gas leakage between the radially superimposed portions of the compressor rotor and the radially internal stator of the associated annular duct which directs the gas downstream into the combustion chamber. Likewise, such loss in energy and efficiency occurs due to gas leakage that passes the rotor / stator or rotor / rotor support with additional problems that include overheating of the support causing excessive use of oil. The conventional gas turbine power generation equipment includes a gas turbine having a honeycomb-labyrinth seal whose hard labyrinth teeth are attached to the radially underlying portion of the compressor and whose honeycomb segment is radially attached to the portion superimposed on the internal stator of the associated annular duct that directs the gas downstream into the combustion chamber. It is known that the hard teeth of the labyrinth will spend a portion of the honeycomb segment due to differential thermal movement during shutdown. Engines of conventional gas turbine aircraft include gas turbines that have used annular brush seals between the stators and the rotors. Although a brush seal provides a better seal than any labyrinth seal (including a honeycomb-labyrinth seal), the free ends of such seals are damaged and worn during engine operation. A known cause is the harmful contact caused by the vibration of the aircraft engine. Another known cause is contact wear caused by differential thermal movement when the motor passes between two different operating states. What is needed is a gas turbine subassembly that has a brush seal and that reduces or eliminates brush seal wear.
Brief Description of the Invention
It is an object of the invention to provide a gas turbine subassembly having a brush seal. In a first preferred embodiment, the gas turbine subassembly of the invention includes a gas turbine stator, a gas turbine rotor, and a generally annular wiper seal. The rotor has first condition of generally stable state and second condition of rotation / load (such as a state of total speed / total load and a state of rotation of gear / no load for a turbine rotor of gas of power plant). The rotor is generally aligned coaxially with and positioned radially in and radially apart from the stator. The rotor includes an outer surface with first and second circumferential portions extending longitudinally and longitudinally joining. The first circumferential portion has a first fabricated diameter that is generally constant over the longitudinal extension of the first circumferential portion. The second circumferential portion (which may be a groove) has a second manofactured diameter which in its entirety is smaller than the first diameter on the longitudinal extension of the second circumferential portion. The rotor and the stator together support a predetermined longitudinal differential thermal radial movement when the rotor undergoes a transition from the first rotation / load state to the second rotation / load state. The brush seal is axially aligned generally with the stator and has a joined end and a free end. The attached end is fixed to the stator and the free end extends into the stator. The free end is located in line-to-line contact with the first circumferential portion when the rotor of the gas turbine is in the first state of rotation / loading and, the predetermined longitudinal differential and radial radial movement includes the free end that moves radially inwardly and longitudinally through the second circumferential portion. A second preferred embodiment is identical to the first preferred embodiment, although the attached end of the brush seal is attached to the rotor, the free end extends outwardly of the rotor, the stator has an internal surface with its first circumferential portion having a first diameter which is generally constant on the longitudinal extension of the first circumferential portion and with its second circumferential portion having a second diameter which in its entirety is larger than the first diameter on the longitudinal extension of the second circumferential portion and the thermal movement includes the free end that moves radially outwardly and longitudinally through the second circumferential portion. A third preferred embodiment is identical to the first preferred embodiment but with the stator replaced by another rotor. A fourth preferred embodiment is identical to the second preferred embodiment but with the stator replaced by another rotor.
Various benefits and advantages derive from the invention. Brush seals are highly efficient seals although they are subject to contact wear that severely degrades their sealing efficiency. In the first preferred embodiment, the gas turbine subassembly of the invention includes a brush seal that is attached to the stator and that makes general line-to-line contact (for high sealing efficiency) with the first circumferential portion of the outer surface of the gas turbine rotor when the rotor is in the first state of rotation / charge (such as a state of total velocity / total charge for a gas turbine rotor of power plant). The second circumferential portion (which may be a groove) has a diameter that is entirely smaller than the diameter of the first circumferential portion so that the brush seal has little (or preferably no) contact wear due to differential thermal movement predetermined (for example, the free end of the brush seal moves into the groove without contacting the gas turbine rotor) during the transition to the second rotation / load state (such as a spin gear state / without charge).
Brief Description of the Drawings
The accompanying drawings illustrate several preferred embodiments of the present invention wherein: Figure 1 is a larger area view in cross sectional side elevation of a first preferred embodiment of the gas turbine subassembly of the present invention that includes a stator, a rotor and a brush seal attached to the stator; Figure 2 is a schematic cross-sectional view of the subassembly of Figure 1 taken along lines 2-2 in Figure 1; Figure 3 is a smaller area cross-sectional elevation view of a second preferred embodiment of the gas turbine subassembly of the present invention that includes a stator, a rotor and a brush seal attached to the rotor; Figure 4 is a smaller area cross-sectional elevation view of a third embodiment of the gas turbine subassembly of the present invention that includes a first rotor, a second rotor positioned within the first rotor, and a bonded brush seal to the first rotor; and Figure 5 is a minor area view in schematic cross sectional side elevation of a fourth preferred embodiment of the gas turbine subassembly of the present invention that includes a first rotor, a second rotor positioned within the first rotor and a seal of brush attached to the second rotor.
Detailed description of the invention
Referring now to the drawings, in which similar numbers represent similar elements in all respects, Figures 1 and 2 schematically show a first preferred embodiment of the gas turbine subassembly 110 of the present invention. The gas turbine subassembly 110 includes a gas turbine stator 112, a gas turbine rotor 114 and a generally annular wiper seal 116. The gas turbine subassembly 110 is a subassembly of a complete gas turbine (not shown) such as a gas turbine of the combustion type that uses the combustion gases to rotate the gas turbine rotor 114 or a gas turbine of the steam type that uses steam to rotate the turbine rotor of the gas 114. Gas turbines are used to supply power to aircraft, ships, tanks, pipe pumps, electric generators. For purposes of illustration, and without limitation, the gas turbine subassembly 110 of the present invention will be described with particular reference to a power plant gas turbine. The gas turbine stator 112 has an axis that extends generally longitudinally 118. In a first preferred construction, the gas turbine stator 112 includes an annular transition duct 120 having radially internal and external stator portions 122 and 124 and a circumferential row of exit guide vanes 126 (only two of which are shown in Figure 1) whose radially inner ends are attached to the radially internal stator portion 122 and whose radially outer ends are attached to the portion radially external stator 124. The gas turbine stator 1 12 further preferably includes a compressor stator enclosure 128 attached to the radially external stator portion 124 of the transition duct and three circumferential rows of the compressor stator vanes 130 which depend radially inward from the stator enclosure of the compressor 128. The direction of the gas flow (in e case air flow), as indicated by the arrows 132, in the gas path of the gas turbine is from the compressor through the transition duct 120 to the combustion chamber (not shown). The gas turbine rotor 14 has first generally stable condition and second rotation / load condition. Preferably, the gas turbine rotor 14 is a power plant gas turbine rotor, the first rotation / load state is a state of total speed / total load and the second state of rotation / load is a state of rotation. spinning gear / no load. The state of total speed / total load is self-explanatory. The state of spin / no-load gear describes a rotor of your gas stream 1 14 which is rotating at a low idle speed by means of an auxiliary motor through a rotating gear. Gas turbine rotors used on ships, aircraft, etc. , have their own conditions of stable state and rotation / load, as is known by the technicians. The gas turbine rotor 114 and the gas turbine stator 112 together experience a predetermined longitudinal differential thermal radial movement when the turbine rotor 114 undergoes a transition from the first rotation / charge state to the second rotation / charge state . Such differential movement can be calculated (or measured) for a particular gas turbine, as can those skilled in the art. The gas turbine rotor 114 is generally coaxially aligned with and radially disposed radially in and radially away from the gas turbine stator 112. The gas turbine rotor 114 is rotatably attached to the gas turbine stator 112 typically by support of bearing elements 134 (only one of which is shown in Figure 1). The gas turbine rotor 114 includes an outer surface 136 with first and second longitudinally extending circumferential portions and longitudinally joined 138 and 140. The first circumferential portion 138 has a first manofactured diameter which is generally constant over the longitudinal extent of the first circumferential portion 138. The second circumferential portion 140 has a second manufactured diameter that is entirely smaller than the first diameter on the longitudinal extension of the second circumferential portion 140. Preferably, the second circumferential portion 140 has a groove shape on the external surface 136 of the gas turbine rotor 114. The second diameter may vary over the longitudinal extent of the groove. In other constructions, the gas turbine rotor may consist of a first enlarged circumferential portion and a second lowered circumferential portion, or the first circumferential portion of the gas turbine rotor may simply be a raised protrusion on the rotor. In a first preferred construction, the gas turbine rotor 114 has a transition rotor segment 142 associated with the transition duct 120, a compressor rotor segment 144 attached to the transition rotor segment 142, and three circumferential rows of compressor rotor blades 146 extending radially outwardly from the rotor segment of the compressor 144. The generally annular wiper seal 116 is generally coaxially aligned with the gas turbine stator 112. The brush seal 116 has a united end 148 and a free end 150. The attached end 148 of the brush seal 116 is attached (directly or indirectly) to the gas turbine stator 112 and, the free end 150 of the brush seal 116 extends into the stator gas turbine 112. In a first preferred construction, the brush seal 116 includes a tie ring 152 and the attached end 148 is a part of the tie ring 152 as shown in Figures 1 and 2. The brush seal 116 comprises a plurality of bristles 154 that are preferably inclined in the rotation direction 156 of the gas turbine rotor 114 as best shown in Figure 2. The free end 150 of the brush seal 116 (ie, the collective free ends of the bristles 154 of the brush seal) is placed in general line-to-line contact with the first circumferential portion 138 of the external surface 136 of the gas turbine rotor 114 when the gas turbine rotor 114 is in the first state of rotation / loading and, the predetermined longitudinal differential and radial radial movement includes the free end 150 of the brush seal 116 (i.e., the collective free ends of the brushes 154 of the wiper seal 116) which moves radially inwardly and longitudinally through the second circumferential portion 140 of the external surface 136 of the turbine rotor ina gas 114, as it is within the design capabilities of the technician based on the teachings of the invention described currently. By "line-to-line" contact is meant that the free end 150 of the brush seal 116 (ie, the collective free ends of the bristles 154 of the brush seal 116) touches only the first circumferential portion 138 of the surface external 136 of turbine rotor 114 without any flexing of (or other interference with) brush seal 116 (ie, bristles 154 of brush seal 116). Preferably, close to the brush seal 116 during the transition (from the first state of rotation / loading to the second state of rotation / loading) the gas turbine stator 112 undergoes the thermal contraction faster than the gas turbine rotor experiences the thermal contraction. Preferably, the preferred groove shape of the second circumferential portion 140 of the outer surface 136 of the gas turbine rotor 114 has a predetermined shape (as is within the design capabilities of the technician based on the teachings of the invention currently described. ) so that the free end 150 of the brush seal 116 (ie the collective free ends of the bristles 154 of the brush seal 116) does not contract the second circumferential portion 140 of the external surface 136 of the gas turbine rotor 114 during the transition (from the first state of rotation / loading to the second state of rotation / loading). The full-cycle longitudinal differential and radial radial movement of the free end 150 of the brush seal 116 (i.e., the collective free ends of the bristles 154 of the brush seal 116) is shown as the dotted path 158 in FIG. labeling of dots 160 representing the relative position of the free end 150 of the brush seal 116 (i.e., the collective free ends of the bristles 154 of the brush seal 116) when the gas turbine rotor 114 is in the first state of rotation / loading and labeling points 162 representing the position of the free end 150 of the brush seal 116 (i.e., the collective free ends of the bristles 154 of the brush seal 116) when the gas turbine rotor 114 is in the second state of rotation / loading. The movement would be along the segment radially inward of the path 158 from the point 160 to the point 162 during the transition from the first state of rotation / loading to the second state of rotation / loading and, the movement along the segment radially outward of path 158 from point 162 to point 160 during a subsequent return to the first state of rotation / loading from the second state of rotation / loading when a complete cycle is completed that starts at the first state of rotation /load. It was noted that particular gas turbines can have three or more different conditions of steady state and rotation / load. A second preferred embodiment of the gas turbine subassembly 210 of the present invention is shown in Fig. 3. The gas turbine subassembly 210 includes a gas turbine stator 212, a gas turbine rotor 214 and, a The generally annular wiper blade 216. The gas turbine stator 212 has a generally longitudinally extending shaft 218 and an inner surface 236 with first and second circumferential portions 238 and 240 extending longitudinally and longitudinally. The first circumferential portion 238 has a first manofactured diameter that is generally constant over the longitudinal extent of the first circumferential portion 238. The second circumferential portion 240 has a second manufactured diameter that is larger in its entirety than the first diameter over the longitudinal extension of the second circumferential portion 240. Preferably, the second circumferential portion 240 has a shape of a groove in the inner surface 236 of the gas turbine stator 212. The gas turbine rotor 214 generally has a first steady state condition and second rotation / load condition. Preferably, the gas turbine rotor 214 is a power plant gas turbine rotor, the first rotation / load state is a total speed / total load state and the second rotation / load state is a gear state rotation / no load. The gas turbine rotor 214 and the gas turbine stator 212 together experience a predetermined longitudinal differential thermal radial movement when the turbine rotor 214 supports a transition from the first rotation / load state to the second rotation / load state . The gas turbine rotor 214 is generally coaxially aligned with and radially in and radially apart from the turbine stator 212. The generally annular wiper seal 216 is generally coaxially aligned with the gas turbine rotor 214. The brush seal 216 has a joined end 248 and a free end 250. The attached end 248 of the brush seal 216 is attached (directly or indirectly) to the gas turbine rotor 214 and the free end 250 of the brush seal 216 is extends outwardly from the gas turbine rotor 214. The free end 250 of the brush seal 216 is placed in general line-to-line contact with the first circumferential portion 238 of the internal surface 236 of the gas turbine stator 212 when the rotor of gas turbine 214 is in the first state of rotation / loading and, the predetermined longitudinal differential and radial radial movement includes the free end 250 of the seal of brush 216 moving radially outwardly and longitudinally through second circumferential portion 240 of internal surface 236 of gas turbine stator 212, as it is within the design capabilities of the technician based on the teachings of the invention currently described. Preferably, close to the brush seal 216 during the transition (from the first state of rotation / loading to the second state of rotation / loading) the gas turbine stator 212 undergoes thermal shrinkage faster than the turbine rotor Gas 214 undergoes thermal contraction. Preferably, the preferred groove shape of the second circumferential portion 240 of the inner surface 236 of the gas turbine stator 212 has a predetermined shape (as is within the design capabilities of the technician based on the teachings of the presently described invention). ) so that the free end 250 of the brush seal 216 does not contact the second circumferential portion 240 of the internal surface 236 of the gas turbine stator 212 during the transition (from the first state of rotation / loading to the second state). rotation / loading). A third preferred embodiment of gas turbine subassembly 310 of the present invention is shown in Figure 4. The description of gas turbine subassembly 310 is identical to the previously given description of gas turbine subassembly 110 of Figures 1 and 2 although with the term "gas turbine stator 112" replaced with "first gas turbine rotor 312" and with the term "gas turbine rotor 114" replaced with "second gas turbine rotor 314". Here, the generally annular wiper seal 316 spans a space between the turbine rotors 312 and 314 and is attached to the first (outer) rotor 312. A fourth preferred embodiment of the gas turbine subassembly 410 of the present invention is shown in FIG. Figure 5. The description of the gas turbine subassembly 410 is identical to the previously given description of the gas turbine subassembly 210 of Figure 3 although with the term "gas turbine stator 112" replaced with "first gas turbine rotor" 412"and with the term" gas turbine rotor 114"replaced with" second gas turbine rotor 414". Here, the generally annular wiper seal 416 spans a space between the turbine rotors 412 and 414 and is attached to the second (internal) rotor 414. The above description of several preferred embodiments of the invention has been presented for purposes of illustration. It is not intended to be thorough or to limit the invention to the precise form described and, obviously, many modifications and variations are possible in the light of the previous teaching. It is intended that the scope of the invention be defined by the claims appended hereto.
Claims (10)
1. A gas turbine subassembly comprising: a) a gas turbine stator having an axis that extends longitudinally generally; b) a gas turbine rotor having first generally stable state condition and a second rotation / load condition and generally coaxially aligned with and radially disposed within and radially apart from the gas turbine stator, wherein the rotor Gas turbine includes an outer surface with first and second circumferential portions extending longitudinally and longitudinally joined, with the first circumferential portion having a first manufactured diameter that is generally constant over the longitudinal extent of the circumferential portion and with the second portion circumferential having a second manufactured diameter that is smaller in its entirety than the first diameter on the longitudinal extension of the second circumferential portion and, wherein the gas turbine rotor and the gas turbine stator together experience differential radial motion and predetermined longitudinal thermal when the rotor undergoes a transition from the first state of rotation / loading to the second state of rotation / loading; and c) a generally annular wiper seal generally coaxially aligned with the gas turbine stator, the wiper seal having a joined end and a free end, with the attached end attached to the gas turbine stator and with the free end extending into the gas turbine stator, wherein the free end is placed in general line-to-line contact with the first circumferential portion when the gas turbine rotor is in the first state of rotation / charge and, where, the predetermined longitudinal differential and radial radial movement includes the free end that moves radially inwardly and longitudinally through the second circumferential portion.
The gas turbine subassembly of claim 1, wherein the gas turbine rotor is a power plant gas turbine rotor, wherein the first rotation / charge state is a state of total speed / load total and the second state of rotation / loading is a state of spin / no-load gear and, where close to the brush seal during the transition the gas turbine stator undergoes thermal shrinkage faster than the turbine rotor of gas undergoes thermal contraction.
3. The gas turbine subassembly of claim 2, wherein the second circumferential portion has a shape of a groove in the outer surface of the gas turbine rotor.
4. The gas turbine subassembly of claim 3, wherein the slot has a predetermined shape so that the free end of the brush seal does not contact the second circumferential portion during the transition.
5. A gas turbine subassembly comprising: a) a gas turbine stator having a generally longitudinally extending shaft and an outer surface with first and second longitudinally extending circumferential portions and longitudinally joined, with the first circumferential portion having a first manofactured diameter which is generally constant over the longitudinal extent of the circumferential portion and with the second circumferential portion having a second manufactured diameter that is larger in its entirety than the first diameter over the longitudinal extent of the second circumferential portion; b) a gas turbine rotor having a first generally stable condition condition and a second rotation / load condition and generally coaxially aligned with and radially disposed within and radially apart from the gas turbine stator, where the gas turbine rotor and the gas turbine stator together experience a predetermined longitudinal differential thermal radial movement when the gas turbine rotor undergoes a transition from the first rotation / charge state to the second rotation / charge state; and c) a generally annular brush seal generally coaxially aligned with the gas turbine stator, the brush seal having a joined end and a free end, with the attached end attached to the gas turbine rotor and with the free end extending into the gas turbine rotor, wherein the free end is placed in general line-to-line contact with the first circumferential portion when the gas turbine rotor is in the first state of rotation / charge and, where, the predetermined longitudinal differential and radial radial movement includes the free end that moves radially inwardly and longitudinally through the second circumferential portion.
The gas turbine subassembly of claim 5, wherein the gas turbine rotor is a power plant gas turbine rotor, wherein the first rotation / charge state is a state of total speed / load total and the second state of rotation / loading is a state of spin / no-load gear and, where close to the brush seal during the transition the gas turbine stator undergoes thermal shrinkage faster than the turbine rotor of gas undergoes thermal contraction.
The gas turbine subassembly of claim 6, wherein the second circumferential portion has a shape of a groove in the inner surface of the gas turbine stator.
The gas turbine subassembly of claim 7, wherein the slot has a predetermined shape so that the free end of the brush seal does not contact the second circumferential portion during the transition.
9. A gas turbine subassembly comprising: a) a first gas turbine rotor having an axis that extends longitudinally generally; b) a second gas turbine rotor having first generally stable state condition and a second rotation / load condition and generally coaxially aligned with and radially disposed within and radially apart from the gas turbine rotor, wherein second the Gas turbine rotor includes an outer surface with first and second circumferential portions extending longitudinally and longitudinally joined, with the first circumferential portion having a first manufactured diameter that is generally constant over the longitudinal extent of the circumferential portion and with the second circumferential portion having a second manufactured diameter that is smaller in its entirety than the first diameter on the longitudinal extension of the second circumferential portion and, wherein the first and second gas turbine rotors together experience differential and thermal radial movement longitudinal default When second the rotor undergoes a transition from the first state of rotation / loading to the second state of rotation / loading; and c) a generally annular wiper seal generally coaxially aligned with the first gas turbine rotor, the wiper seal having a joined end and a free end, with the attached end attached to the first gas turbine rotor and with the free end extending into the first rotor of your gas container, where the free end is placed in general line-to-line contact with the first circumferential portion when the second gas turbine rotor is in the first state of rotation / loading and, wherein, the predetermined longitudinal differential radial and thermal movement includes the free end that moves radially inwardly and longitudinally through the second circumferential portion. A gas turbine subassembly comprising: a) a first gas turbine rotor having a generally longitudinally extending shaft and an inner surface with first and second longitudinally extending circumferential portions and longitudinally joined together, with the first circumferential portion having a first manometer diameter that is generally constant over the longitudinal extension of the circumferential portion and with the second circumferential portion having a second manofactured diameter which is larger in its entirety than the first diameter over the circumferential portion. longitudinal extension of the second circumferential portion; b) a second gas turbine rotor having a first condition of generally stable state and a second condition of rotation / load and generally coaxially aligned with and radially disposed within and radially apart from the first gas turbine rotor, wherein the first and second gas turbine rotors and the gas turbine stator together experience a predetermined longitudinal differential thermal radial movement when the second gas turbine rotor undergoes a transition from the first rotation / charge state to the second state of rotation / loading; and c) a generally annular wiper seal generally coaxially aligned with the second gas turbine rotor, the wiper seal having a joined end and a free end, with the attached end attached to the second gas turbine rotor and with the free end extending into the second gas turbine rotor, wherein the free end is placed in general line-to-line contact with the first circumferential portion when the second gas turbine rotor is in the first state of rotation / charge and , wherein, the predetermined longitudinal differential radial and thermal movement includes the free end that moves radially outwardly and longitudinally through the second circumferential portion. SUMMARY A gas turbine subassembly that has a stator, a rotor and, a brush seal that is attached to the stator whose free end is in line-to-line contact with a first circumferential portion of the outer surface of the rotor during a first rotation / load state (such as a state of full speed / total load of a gas turbine rotor of power plant). A second circumferential portion that joins longitudinally (such as a groove) has a diameter smaller than that of the first circumferential portion. The rotor and the stator together experience a predetermined thermal and differential movement when the rotor transits to the second state of rotation / load (such as a spin / non-load state). During such movement, the free end of the brush seal moves radially inwardly and longitudinally through the second portion, preferably without any contact, to minimize or eliminate wear of the brush seal.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/642,289 US5613829A (en) | 1996-05-03 | 1996-05-03 | Gas turbine subassembly having a brush seal |
| US08642289 | 1996-05-03 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| MXPA97003218A true MXPA97003218A (en) | 1998-04-01 |
| MX9703218A MX9703218A (en) | 1998-04-30 |
Family
ID=24575990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| MX9703218A MX9703218A (en) | 1996-05-03 | 1997-04-30 | Gas turbine subassembly having a brush seal. |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US5613829A (en) |
| EP (1) | EP0805264B1 (en) |
| JP (1) | JP3977482B2 (en) |
| CA (1) | CA2202952C (en) |
| DE (1) | DE69711480T2 (en) |
| MX (1) | MX9703218A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2070700B (en) * | 1980-03-01 | 1983-10-05 | Rolls Royce | Gas turbine seals |
| US5074748A (en) * | 1990-07-30 | 1991-12-24 | General Electric Company | Seal assembly for segmented turbine engine structures |
| GB2258277B (en) * | 1991-07-29 | 1995-02-22 | Europ Gas Turbines Ltd | Brush seals |
| US5181728A (en) * | 1991-09-23 | 1993-01-26 | General Electric Company | Trenched brush seal |
| US5400586A (en) * | 1992-07-28 | 1995-03-28 | General Electric Co. | Self-accommodating brush seal for gas turbine combustor |
| US5265412A (en) * | 1992-07-28 | 1993-11-30 | General Electric Company | Self-accommodating brush seal for gas turbine combustor |
| US5474306A (en) * | 1992-11-19 | 1995-12-12 | General Electric Co. | Woven seal and hybrid cloth-brush seals for turbine applications |
| US5480162A (en) * | 1993-09-08 | 1996-01-02 | United Technologies Corporation | Axial load carrying brush seal |
| US5433453A (en) * | 1994-03-02 | 1995-07-18 | Imo Industries, Inc. Quabbin Division | Articulated snout rings having spaced teeth |
-
1996
- 1996-05-03 US US08/642,289 patent/US5613829A/en not_active Expired - Lifetime
-
1997
- 1997-04-17 CA CA002202952A patent/CA2202952C/en not_active Expired - Fee Related
- 1997-04-23 JP JP10546297A patent/JP3977482B2/en not_active Expired - Fee Related
- 1997-04-30 MX MX9703218A patent/MX9703218A/en not_active IP Right Cessation
- 1997-05-02 EP EP97303057A patent/EP0805264B1/en not_active Expired - Lifetime
- 1997-05-02 DE DE69711480T patent/DE69711480T2/en not_active Expired - Lifetime
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