Patent Application
20250047162
Exemplary embodiments pertain to the art of seals and, in particular to a non-contacting gas seal.
Dry gas seals are typically used to seal centrifugal compressors that are often used in transportation and distribution of gasses such as natural gas. For instance, in a natural gas pipeline, compressors may be located at set intervals to boost the gas pressure for processing, to counter the effect of flow losses along the transmission pipelines, and to generally keep the gas moving towards its destination.
In general, dry gas seals operate by providing a seal between a rotating ring and a stationary ring. The rotating ring is sometimes referred to as a “mating ring” as it is mated to the rotating shaft/rotor. The rotating ring can be mated to the rotor via a shaft sleeve. The stationary ring can sometimes be referred to as the primary ring and does not rotate during operation. In operation, a layer of gas is developed between the two rings that forms a seal while allowing the rings to move relative to one another without contacting each other. The gas layer is formed from process or sealing gas injected into the dry gas seal.
When installed into a compressor, such dry gas seals may be located next to or near a bearing or bearing cavity of the compressor or other machinery. These bearings can be lubricated by and operate with, for example, oil or another liquid lubricant.
A separation seal can serve to prevent or reduce oil or other lubricants of the bearing from entering the dry gas seal. In the typical separation seal, a separation gas is injected between two bushings to create a pressure barrier between the bearing and the dry gas seal. In more detail, a typical separation seal includes an inlet into which the separation or buffer gas is provided. The separation gas escapes axially outward in both the in-board and outboard directions. The gas is provided between two bushings that can either contact the shaft (or a sleeve placed thereon) in a contact separation seal or be slightly separated from the shaft in a non-contacting separation seal.
Disclosed is a seal for preventing fluid from entering a dry gas seal surrounding a shaft of a rotating machine. The seal can be any type of dry gas seal including but not limited to a main seal and a separation seal.
In one embodiment, a separation seal for preventing fluid from entering a dry gas seal surrounding a shaft of a rotating machine is disclosed. The separation seal of this embodiment includes a stator configured to be fixedly attached to the rotating machine such that it surrounds the shaft, the stator including a primary ring control chamber formed therein. The seal also includes a primary ring having a back, a first thrust ring at least partially within the primary ring control chamber and coupled to the primary ring, a mating ring coupled to the shaft that rotates with the shaft and relative to the primary ring, and one or more biasing members that urge the primary ring toward the mating ring to form a seal interface between primary ring and the mating ring. The stator includes a passageway constructed and arranged to convey pressurized buffer gas at a gas pressure in normal operation to the primary ring control chamber. The primary ring is configured such that the pressurized buffer gas in the primary ring control chamber passes from the back of the primary ring, through the primary ring and to the seal interface. The buffer gas that reaches the seal interface passes, in normal operation, both radially inward and radially outward along the seal interface. In one embodiment, one of the mating ring and the primary ring includes grooves formed on a face thereof. In the event of a buffer gas delivery pressure reduction, the grooves pump gas from an inner diameter of the seal interface to an outer diameter of the seal interface.
In any embodiment herein, the primary ring is formed of carbon or another material. The material can have had pores therein filled or sealed to form a non-porous primary ring.
In addition to or as an alternative the any prior embodiment, the seal can further include one or more sealing elements disposed between the first thrust ring and the back of the primary ring and within the primary ring control chamber.
In addition to or as an alternative the any prior embodiment, the sealing elements are spaced apart from the back of the primary ring by a separating member.
In addition to or as an alternative the any prior embodiment, the separating member is a ring.
In addition to or as an alternative the any prior embodiment, the separating member is a second thrust ring.
In addition to or as an alternative the any prior embodiment, the seal can also include one or more secondary sealing elements disposed between the second thrust ring and the back of the primary ring.
In addition to or as an alternative the any prior embodiment, the one or more secondary sealing elements are not in the primary ring control chamber and do not contact a side of the primary ring control chamber.
In addition to or as an alternative the any prior embodiment, the back of the primary ring includes one or move grooves formed therein to receive the one or more sealing elements.
In addition to or as an alternative the any prior embodiment, the one or more sealing elements include a first sealing element and a second sealing element and wherein the first and second sealing elements are O-rings having different cross-sectional diameters.
Also disclosed is an assembly for sealing a fluid in a rotating machine. The assembly includes a primary dry gas seal adapted and configured to surround a shaft of the rotating machine and prevent the fluid from exiting the rotating machine; and a secondary seal connected to the primary dry gas seal adapted and configured to prevent a liquid from entering the dry gas seal. The secondary seal can be any seal disclosed above or otherwise herein.
The specifics of the exclusive rights described herein are particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the embodiments of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The diagrams depicted herein are illustrative. There can be many variations to the diagram or the operations described therein without departing from the spirit of the invention. For instance, the actions can be performed in a differing order or actions can be added, deleted or modified. Also, the terms “connected,” “coupled” and the like and variations thereof describes having a communications path between two elements and does not imply a direct connection between the elements with no intervening elements/connections between them. All of these variations are considered a part of the specification.
A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
Disclosed herein is a seal that includes a primary ring. The primary ring includes one or more micro-drilled holes formed in a face thereof. The seal can be a standalone seal that operates, for example, as a separation seal. Alternatively, the seal can be operated as a containment or back-up seal to a primary dry gas seal. In both cases, the primary ring is either directly or indirectly coupled to a thrust ring. In normal operation, a buffer or separation gas is provided to the seal, the gas passes through the thrust ring and through a channel formed in a back of the primary ring. The channel (or pilot hole) does not extend all way to the face of the primary ring. Rather, a small (e.g., micro-drilled) holes drilled in face and provides a fluid passageway between the face and the channel. Thus, gas that enters the channel is allowed to pass through the one or more small holes (or microchannels) to the face of the primary ring. A ratio of the size of the channel and microchannel can be from 10-100. That is, in one embodiment, the channel can have a diameter that is 10-100 times larger than the diameter of the microchannels. Each channel can, in one embodiment, have more than one microchannel that connect it to the face.
Herein, the primary ring shall be formed of, for example, graphite, carbon, silicon carbide, Tungsten carbide, alumina. The ring is treated, as is well known in the art, by filling or sealing pores in such material such the ring is non-porous. Thus, the rings herein are filled and non-porous.
To address situations where the gas flow may be reduced (e.g., below a threshold that will independently keep the rings from contacting each or that can support the thin film), the mating ring may have grooves formed thereon that pump gas between the faces to prevent them from contacting. In the separation seal usage case, the thrust ring can be a single or a split thrust ring.
In cases where the seal is used as a containment seal, in normal operation the seal operates generally as above. This allows for long running, non-contacting back-up seal. The mating ring may have (but does not have to have) the above-described grooves.
In such a case, while both single and split thrust rings may be utilized, in one embodiment, the thrust ring is a split thrust ring that includes two portions that are typically mated but can be separated. If the primary dry gas seal has in increase in gas passing between the rings (e.g., above a pressure that can typically vented out through, for example a choke in the vent), the pressure of the gas escaping from the primary seal will cause the portions of the thrust ring to separate (e.g., the lower/inner thrust ring described below moves away from the primary ring). The upper/outer thrust ring takes over and creates a new balance diameter. The grooves on the mating ring will take over and draws high pressure gas from the dry gas seal side and pump it through the sealing interface (e.g., between the face of the primary and mating rings) to create a level of flow towards the bearing side. The result is the maintenance of a positive restriction to prevent or reduce leakage of pressurised gas. While described as a “back-up” seal, it shall be understood that such a seal may serve a dual purpose as a back-up seal and a separation seal. This can allow for a single seal unit to be provided that does not need an additional separation seal.
In one use, the seal 100 is intended to be located between a dry gas seal 107 and a bearing cavity 108. Herein, the seal 100 shall be referred to as having an inboard (or seal) side 103 and an outboard (or bearing) side 105. The inboard side 103 is typically disposed proximate a dry gas seal 107 and the outboard side 105 is typically disposed proximate a bearing or bearing cavity 108 containing a bearing. This is, however, not a required orientation of elements. As will be understood, the seal 100 and the dry gas seal 107 can be included as part of a cartridge that can include one or more separation and dry gas seal elements. Examples of dry gas seals can be found in the prior art and the dry gas seal 107 can be any type of dry gas seal. The same is true of the bearings in the bearing housing.
Both the seal 100 and the dry gas seal 107 are arranged and designed to be attached to shaft 102. Herein, the term shaft will generally be used to refer to a shaft of a turbo-compressor. The teachings herein can be applied, however, to any rotating machine and the shaft may or may not include a sleeve thereon. In the case where a sleeve is provided, the term “shaft” shall include the combination of the shaft and the sleeve.
From time-to-time certain directions will be used herein. An outboard direction is the direction extending in the direction of arrow A and the inboard direction (e.g., towards the dry gas seal 107 or the process chamber 106 described below) is in the opposite direction as indicated by arrow A′. The radially inward direction is in the direction of arrow B which is directed toward a center of the shaft 102 and the radially outward direction is in the opposite direction as indicated by arrow B′.
At least a portion of the seal 100 is positioned between a rotating compressor shaft 102 and a compressor housing 104. The seal 100 is also positioned between the bearing cavity 108 and the gas seal 107 to keep bearing oil from impinging in the gas seal 107 in one embodiment.
The rotating compressor shaft 102 is generally part of a compressor and is operably coupled to a compressor impeller (not shown) disposed in a process cavity 106 of the compressor, and is supported by the housing 104 via a bearing (not shown) disposed in a bearing cavity 108 of the housing 104. The rotating compressor shaft 102 is the rotor of the compressor in most instances and may be referred to simply as a rotating shaft from time to time herein. It shall be understood that the rotating shaft need not be the rotor of the compressor itself but could be any shaft connected to the rotor that rotates with it around which a seal should be provided.
The compressor housing 104 includes a bore 109 formed in it that extends between a process cavity 106 and a bearing cavity 108 and defines an annular seal chamber 112 into which the seal 100 and the dry gas seal 107 may be inserted. The process cavity 106 includes the gas (typically a hydrocarbon) being compressed by the compressor. That gas is referred to as process gas herein.
The seal 100 includes a stator 117 that can be formed of one or more components and joined in a fixed relationship to one another as well as with the compressor housing 104 when installed. As shown, the stator 117 is formed as a retainer ring that can be sealed to the compressor housing 104 by any sealing element such as a radial seal 119.
The seal 100 can also include a sleeve ring 115 that can be formed of one or more components and that is attached to the rotating shaft 102 such that it rotates with the rotating shaft 102. The illustrated separation seal sleeve ring 115 includes two portions 115a, 115b in
Assuming the process gas in the process cavity 106 is under pressure, all components of the seal 100 and the dry gas seal 107 are urged in the outboard direction A toward thrust/retaining rings 121/125 during operation. Axial movement of the sleeve ring 115 relative to the rotating shaft 102 is limited by a shaft thrust ring 125 received in a groove in the rotating shaft 102. Axial movement of the stator 117 is limited by stator thrust ring 121 received in a groove in the housing 104.
In the above example, it should be understood that the shaft thrust ring 125 can be fixed relative to the sleeve ring 115 so that the two elements rotate together. Also, for sake of completeness, it shall be understood that other elements can be attached to the sleeve ring 115 to provide support or other functions but are not specifically described herein.
The sleeve ring 115 carries and otherwise mates rotating or mating ring 114 to the rotating shaft 102. That is, the sleeve ring 115 being mated to the rotating shaft 102 allows the mating ring 114 to also rotate with the shaft 102. The mating ring 114 can include one or more grooves 191 formed on a face thereof. As noted below, grooves can additionally or alternatively be on the primary ring. The grooves can be selected from any type of groove known in the art or later developed including, spiral and bi-direction grooves.
During operation, gas 140 in the process cavity 106 that passes through the seal interface formed by mating/primary rings in the dry gas seal can exit a vent 174 in the compressor housing 104.
The seal 100 impedes oil from the bearing cavity 108 from reaching the gas seal 107 in a manner that is similar to how a dry gas seal works. In particular, as with a typical separation seal, the seal 100 keeps the oil from traveling inboard due to the interaction of the mating ring 114 and a primary ring 116. The primary ring 116 can also be referred to as a stationary ring as it does not rotate with the shaft and is thus, generally or completely, rotationally stationary relative to the housing 104 during operation. Reference numeral 113 identifies the location of the seal interface formed between the mating ring 114 and the primary ring 116.
As will be understood by the skilled artisan, the primary ring 116 is axially movable relative to the housing 104 during operation such that a controlled distance may be maintained between the mating ring 114 and the primary ring 116 at the rotating seal interface 113. In the illustrated embodiment, a force is applied to the primary ring 116 by one or more biasing members 138. The mating/primary rings are non-porous in one embodiment and the holes discussed below are drilled into the non-porous ring.
During operation, a flow of a gas sometimes referred to as “buffer gas” is provided to a back side 180 of the primary ring 116 via a buffer gas passage 182. The buffer gas passage 182 can receive the gas from a buffer gas inlet 184 formed in the compressor housing 104.
As generally shown by arrows 150, this gas passes through the primary ring 116 and exits it at or near the seal interface 113 at primary ring face 116a. This gas, in normal operation as shown in
With reference now to both
As shown, a thrust ring 202 is disposed in the primary ring control chamber 201. The thrust ring 202 includes a passage 203 formed therein that allows the buffer gas 150 to pass through it allowing it to reach the back side 180 of the primary ring 116. The passage 203 can be sized such that gas in buffer gas passage 182 passes through and equalizes pressure on both sides of the thrust ring 202 over time. Based on this pressure balance, both the biasing members 138 and the gas in the primary ring control chamber 201 serve to resist motion of the mating ring in the inboard direction (e.g., opposite of direction A).
In one embodiment, the primary ring 116 is formed of graphite, carbon, silicon carbide, Tungsten carbide, alumina or basically any porous and or sintered material. These materials are typically found as face seals and mechanical seals and as runners and runner faces in dry gas seals and can have pores within them. Herein, and as opposed to a porous primary ring, the pores are filled or sealed in one embodiment so that gas cannot pass from the back side 180 of primary ring 116 to it sealing face 116a except through channels or other paths formed therein.
As shown in
Rotation of the mating ring 114 due to its connection to the rotating shaft 102 will cause some of the buffer gas at the seal interface 113 to be drawn toward the OD. However, due to the pressure of the buffer gas, the gas can travel between the faces towards both the inner and outer diameters of the mating ring 114/primary ring 116 such that it travels in the manner described above. The presence and pressure of the buffer gas 150 at the seal interface 113 and the relative motion of the mating/primary rings 114, 116 results in a so-called “lift off” resulting in physical separation of the rings.
During normal operation, as described above, pressure in the process cavity 106 as well as heat can cause the rotating shaft 102 to move or expand axially. The biasing members 138 can allow for the primary ring 116 to keep a constant distance during operation between itself and the mating ring 114 even as the mating ring 114 moves axially due to such movement of the rotating shaft 102.
One or more radial seals 205 may be provided to direct the buffer gas 150 so that gas leaving the primary ring control chamber 201 travels through the seal interface 113 (e.g., between the primary ring 116 and the stator 117). The seals may be formed of a polymer or an elastomer and one example of such a seal is a lip seal. In
With reference now to
With reference now to
In the embodiment shown in
The mating ring 114 can include grooves 191 formed therein that draw gas from the inner diameter into the seal interface 113. As more fully described below, these grooves 191 may help to prevent the mating and primary rings 114, 116 from contacting one another in the event that gas flow of the buffer gas ceases or becomes otherwise ineffectual at forming a gas film between the mating and primary rings 114, 116. The grooves can alternatively be on the primary ring, for example, as illustrated below.
The shape of the grooves 191 is optimized to enhance seal performance. As is known in the art, the grooves 191 typically are machined or etched only to the radial midpoint of the face of the mating ring 114 and have a very shallow depth of only a few microns. The grooves are shaped to have a tip such that gas enters the grooves is compressed because of the volume reduction at the tips.
In the above examples, it shall be understood that in normal operation high pressure buffer gas 150 flows through the primary ring 116 to its face 116a via channel 199 and that microchannels in the termination region 196 to reach the seal interface 113. In such operation, the buffer gas 150 leaves the interface towards both the bearing and dry gas seal sides (e.g., radially inwardly and radially outwardly). Due to the presence of the grooves 191, potentially, greater flow of the buffer gas 150 is directed radially outward towards the bearing cavity 108 which provides a greater restriction against the bearing oil.
Regardless of particular flow, the pressure from the buffer gas 150 present at the seal interface 113 after passing the through the primary ring 116 creates a thin film (and separation/gap) between the mating and primary rings 114, 116. Such separation can create a non-contacting regime of operation. Further, the pressure of the buffer gas 150 as provided from the inlet 184 can allow for a much greater film stiffness that in a typical non-contacting seal and may provide greater back pressure to resist against oil ingress from the bearing side
Embodiments of the present invention may also effectively operate in situations wherein supply of buffer gas 150 is diminished. With reference now to
In all of the prior examples the thrust ring 202 has been shown as being formed of two separate pieces (e.g., outer and inner thrust rings 202a/202b). However, the ring can be formed as a single piece. An example of such a single piece ring 202 is shown in
Similarly, gas that exits the seal interface 113 as the OD of the primary ring 116 can traverse the outboard passageway 502 in the outboard direction A. This gas can be released via vent 174 (
In
The rings 202a, 202b are preferably shaped and arranged such that, when mated, one or more passageways exist between them through which buffer gas 150 described above can pass. The rings 202a, 202b shown in
Inner and outer seals (e.g., o-rings 205a, 205b), are disposed between the respective inner and outer rings 202a, 202b and the back 620 of the primary ring 116. These seals can serve to seal the back section 314 of the primary ring 116 in the primary ring control chamber 201 in this embodiment.
With reference to
As above and with reference now to
The buffer gas 150 travels through the primary ring 116 and exits at the primary ring 116 at its face 116a (e.g., at the seal interface 113 formed between the mating and primary rings 114/116).
As discussed in the above examples, the embodiments herein include primary ring control chamber 201 that includes at least one thrust ring 202 disposed at least partially therein. Further, as shown in
The seal shown in
With reference to both
The first thrust ring 202 can either be formed as a single ring with one or more passages 203 (e.g., holes) formed therein. Of course, it could be formed as a split ring as described above. As illustrated, all of the first thrust ring 202 is disposed in the primary ring control chamber 201. The seal 100 includes first and second sealing elements 205a, 205b. These can be any type of sealing elements and, as illustrated, are formed as o-rings. The first and second sealing elements 205a, 205b direct the gas in primary ring control chamber 201 through the passage 203 formed in the first thrust ring 202. The first and second sealing elements 205a, 205b also form a seal between the first thrust ring 202 and the second thrust ring 720 so that barrier gas in primary ring control chamber 201 is directed through the back 180 of the primary ring 116 and then through the primary ring 116 to the face 116a.
As shown best in
In general, the embodiment shown in
As above and with reference now to
The buffer gas 150 passes through the first and second thrust rings 202, 720 and then travels through the primary ring 116 via channel 190 exits at the primary ring 116 at its face 116a (e.g., at the seal interface 113 formed between the mating and primary rings 114/116).
In the case a reduction in buffer gas supply, the seal will operate as described above with respect to
In the prior description the seal including a primary ring was illustrated as a separation seal that was separate from the dry gas seal. In another embodiment, and a shown in
At least a portion of the dry gas seal assembly 900 is positioned between a rotating compressor shaft 102 and a compressor housing 104. The rotating compressor shaft 102 is generally part of a compressor and is operably coupled to a compressor impeller (not shown) disposed in a process cavity 106 of the compressor and is supported by the housing 104 via a bearing (not shown) disposed in a bearing cavity 108 of the housing 104. The rotating compressor shaft 102 is the rotor of the compressor in most instances and may be referred to simply as a rotating shaft from time to time herein. It shall be understood that the rotating shaft need not be the rotor of the compressor itself but could be any shaft connected to the rotor that rotates with it around which a seal needs to be provided.
The compressor housing 104 includes a bore 109 formed in it that extends between the process cavity 106 and the bearing cavity 108 and defines an annular seal chamber 112 into which the dry gas seal assembly 900 may be inserted. The process cavity 106 includes the gas (typically a hydrocarbon) being compressed by the compressor. That gas is referred to as process gas herein.
An optional shroud not shown that may include a labyrinth seal and which extends over a radially extending opening formed between the rotating shaft 102 and the compressor housing 104 may be provided to inhibit the free flow of process gas from the process cavity 106 into the bore 109. The shroud 126 is disposed in the bore 109 and, as illustrated carries a labyrinth seal 128 that serves to totally or partially prevent the free flow of process gas from the process cavity 106 into the bore 109. The combination of the shroud 126 and the labyrinth seal 128 extends over a radially extending opening formed between the rotating shaft 102 and the compressor housing 104. As illustrated, the shroud 126 and the labyrinth seal 128 are shown as two separate items but they could be formed as an integrated unit in one embodiment. The dry gas seal assembly 900 illustrated in
The cartridge can also include a sleeve ring 115 that can be formed of one or more components and that that is attached to the rotating shaft 102 such that it rotates with the rotating shaft 102. The illustrated sleeve ring 115 includes four portions 915, 917, 919, 921. The first portion 915 carries rotating portions of the first seal 902 and the fourth portion 921 carries rotating portions of the secondary seal 904. As shown, two spacer rings 917, 919 are located between the first and second portions of the sleeve ring. The portions can be formed as rotating rings configured to contact and rotate with the rotating shaft 102. Of course, the sleeve ring could be formed as a unitary piece or could include any number of pieces that are either joined together or otherwise held stationary relative to each other during operation (e.g., all pieces rotate together as one).
If the process gas in the process cavity 106 is under pressure, all components of the dry gas seal assembly 900 are urged in the direction toward thrust rings 121 and 125 (direction A) during operation. Axial movement of the primary dry gas seal 902 relative to the rotating shaft 102 is limited by a shaft thrust ring 125 received in a groove in the rotating shaft 102.
In the above example, it should be understood that the shaft thrust ring 125 can be fixed relative to the sleeve rings so that the two elements rotate together. Also, for sake of completeness, it shall be understood that other elements can be attached to the sleeves to provide support or other functions but are not specifically described herein.
The portion 915 carries and otherwise mates first seal rotating or mating ring 914 to the rotating shaft 102. That is, the portion 915 is mated to the rotating shaft 102 allows the first seal mating ring 914 to also rotate with the shaft 102. First mating ring 914 can include one or more grooves (not shown) formed on a face thereof.
It shall be understood that during normal operation the secondary seal 904 operates in the same manner as described above with respect to
During operation, gas present in the process cavity 106, which can reach pressures of 6,500 PSI-G (450 BAR-G) or above, is sealed from the bearing cavity 108 and from the environment by the interaction of the first seal mating ring 914 and a first seal primary ring 916. The first seal primary ring 916 can also be referred as a stationary ring as it does not rotate with the shaft and is thus, generally or completely, rotationally stationary relative to the housing during operation. Reference numeral 913 identifies the location of the seal interface formed between the first seal mating ring 914 and the first seal primary ring 916.
As will be understood by the skilled artisan, the first seal primary ring 916 is axially movable relative to the housing 104 during operation such that a controlled distance may be maintained between the first seal mating ring 914 and the first seal primary ring 916 at the seal interface 913. In the illustrated embodiment, a spring force is applied to the first seal primary ring 916 by one or more biasing members 938 disposed between a retainer ring 917a and the first seal primary ring 916. As shown, the biasing members 938 are disposed between the stator 917 and a carrier ring 970 that is attached to or otherwise contacts the first seal primary ring 916. The skill artisan will realize that in different types of seals, the primary/first seal design and geometry may be varied from that shown in
During operation, some of the process gas travels between the seal interface 913 of the first seal mating and primary rings 914, 916. The process gas that so travels is identified by arrow 950.
In more detail, of rotation of the first seal mating ring 914 due to its connection to the rotating shaft 102 and/or pressure of the process gas in the process chamber 106 will cause some of the process gas to be drawn from an outer diameter of the first seal mating ring 914 into the groves formed therein. The shape of the grooves is optimized to enhance seal performance. As is known in the art, the grooves typically are machined only to the radial midpoint of the face of the first seal mating ring 914 and have a very shallow depth of only a few microns. The grooves can be shaped to have a tip such that gas enters the grooves is compressed because of the volume reduction at the tips. The area of slightly higher gas pressure creates a pressure dam and results in a so-called “lift off” resulting in physical separation of the primary and mating rings 914, 916. As such, in operation, gas flows over the dam area (between the primary and mating rings 914, 916) to a low-pressure side 960 of the first seal interface 913. Gas that passes through the seal interface can exit the dry gas seal assembly 100 via a vent 974 in the compressor housing 104.
To allow for the above described lift off, the carrier ring 970 is provided as a means for allowing the required movement. The carrier ring 970 is coupled to the stator 917 by the biasing members 938. The biasing members 938 can be a singular element or composed of a plurality elements. The biasing members 938 are comprised of one or more springs in one embodiment. Of course, the shape and design of the carrier ring in the first seal can be varied.
During operation, as described above, pressure in the process cavity 106 as well as heat can cause the rotating shaft 102 to move or expand axially. The biasing members 938 can allow for the first seal primary ring 916 to keep a constant distance during operation between itself and the first seal mating ring 914 even as the mating ring 914 moves axially due to such movement of the rotating shaft 102.
As mentioned above, the secondary seal 904 receives a flow a buffer gas. It shall be understood that the secondary seal can be formed in the same or similar to any prior disclosed embodiment of
The gas, after passing through the seal interface 113 travels both radially and axially outward to the bearing cavity 108 and radially and axially inward (direction A′) towards the process cavity 106. In
In normal operation, the pressure in the vent 974 is roughly atmospheric or slightly higher. In the event that the buffer gas flow is reduced, the secondary seal 904 will operate in the manner as described above with respect to
In the event that the primary seal 902 is leaking, and now with reference to
The high-pressure process gas 950 can also cause the inner thrust ring 202a and inner seal 205a to be pushed axially inward as illustrated in
After the pressure has stabilized in the primary ring control chamber 201, the outer thrust ring 202 defines a new balance diameter of the secondary seal 904 and grooves 191 in the mating ring 114 will draw the high-pressure process gas 950 from the ID and through the sealing interface 113 to create level flow towards the bearing chamber 108. In this manner, the secondary seal 904 can maintain a positive restriction in this catastrophic event and prevent extreme leakage of pressurised gas into the atmosphere.
There are several variations that can applied to the teachings herein. For example, the radial seals 205 of any prior embodiment can be implemented as o-rings. These o-rings can have different diameters. As shown in
In
In another embodiment, and as shown in
It shall be understood that additional variations in the back of the primary ring are contemplated. For instance, grooves 1302a/1302b can be formed in the back 180 of the primary ring 116 as shown in
In the prior embodiments having grooves in the back of the primary ring 116, it should be understood that one of the grooves could be omitted. Further, in such cases, while not required, one of more of the outboard faces of the thrust ring could be adjusted so that it does not include a receiving area for an o-ring (
In
For sake of completeness,
In any of the non-porous primary rings discussed herein the face can be arranged in different manners. In the above example, it was noted that the mating ring 114 includes the grooves 191. As shown in
In one embodiment, the mating ring 114 or primary ring 116 can include both “pumping” grooves and separation grooves that extend from the location of the micro-drilled holes (referred to as a central channel) partially to the either the ID or the OD of the rings 114/116.
A section of a face of such ring is shown in
In particular, the face 1700 includes the central channel 1702. If the central channel 1702 is on the primary ring, it is defined in the locations where the holes are formed and may or may not depressed from a surface of the face 1700. An example of such a channel is shown above as element 199 in
If the central channel 1702 is on the mating ring, it is defined such that it is arranged so that overlaps where the holes on the primary ring are formed and may or may not depressed from a surface of the face 1700.
The face 1700 defines a low DAM width, an upper DAM width, a radial face width and a channel width as shown in
Various embodiments of the invention have been described herein with reference to the related drawings. Alternative embodiments of the invention can be devised without departing from the scope of this invention. Various connections and positional relationships (e.g., over, below, adjacent, etc.) are set forth between elements in the following description and in the drawings. These connections and/or positional relationships, unless specified otherwise, can be direct or indirect, and the present invention is not intended to be limiting in this respect. Accordingly, a coupling of entities can refer to either a direct or an indirect coupling, and a positional relationship between entities can be a direct or indirect positional relationship. Thus, any coupling or connection herein may later be called direct in the claims below even if not specifically recited in that manner above. Moreover, the various tasks and process steps described herein can be incorporated into a more comprehensive procedure or process having additional steps or functionality not described in detail herein.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
This application claims the benefit of an earlier filing date from U.S. Provisional Application Ser. No. 63/529,868 filed Jul. 31, 2023, the entire disclosures of both which are incorporated herein by reference.
| Number | Date | Country | |
|---|---|---|---|
| 63529868 | Jul 2023 | US |
