US20220259981A1 - Erosion mitigating labyrinth seal mating ring - Google Patents
Erosion mitigating labyrinth seal mating ring Download PDFInfo
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- US20220259981A1 US20220259981A1 US17/176,606 US202117176606A US2022259981A1 US 20220259981 A1 US20220259981 A1 US 20220259981A1 US 202117176606 A US202117176606 A US 202117176606A US 2022259981 A1 US2022259981 A1 US 2022259981A1
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- seal
- impeller
- pathway
- airflow
- compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/12—Shaft sealings using sealing-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/12—Shaft sealings using sealing-rings
- F04D29/126—Shaft sealings using sealing-rings especially adapted for liquid pumps
- F04D29/128—Shaft sealings using sealing-rings especially adapted for liquid pumps with special means for adducting cooling or sealing fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
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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
- F16J15/44—Free-space packings
- F16J15/447—Labyrinth packings
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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
- F05D2240/20—Rotors
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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
- F05D2240/50—Bearings
-
- 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
- F05D2240/60—Shafts
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/185—Two-dimensional patterned serpentine-like
Definitions
- Exemplary embodiments pertain to the art of environmental control units for, for example, aircraft.
- CAC cabin air compressor
- erosion damage occurs to a bearing support housing downstream of the compressor impeller. This erosion damage occurs when foreign object particles bypass a labyrinth seal between the impeller and the bearing support housing and subsequently impact the bearing support housing. Such erosion of the bearing support housing shortens the service life of the bearing support housing specifically and the cabin air compressor in general.
- a compressor assembly includes an impeller rotatable about a central axis and a seal assembly.
- the seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed.
- the seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis.
- a plurality of tortuous pathways are formed in a downstream surface of the seal support ring and are configured to diffuse a tangential component of the airflow.
- the plurality of tortuous pathways is circumferentially spaced.
- a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet.
- the pathway inlet is located radially inboard of the pathway outlet.
- a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
- the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
- a shaft is operably connected to the impeller, and a bearing assembly includes a bearing supportive of the shaft and a bearing support housing into which the bearing assembly is installed.
- the seal support ring is located axially between the impeller and the bearing support housing.
- the deflector ramp deflects the airflow from impacting on the bearing support housing.
- the seal support ring is installed to the bearing support housing.
- the sealing element of the impeller is located at a sealing flange of the impeller extending axially from the impeller.
- a cabin air compressor in another embodiment, includes a compressor housing having an inlet and an outlet, and an impeller located in the housing.
- the impeller is rotatable about a central axis and is configured to compress an airflow directed through the inlet and direct the compressed airflow to the outlet.
- a seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed.
- the seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis.
- a plurality of tortuous pathways are formed in a downstream surface of the seal support ring and configured to diffuse a tangential component of the airflow.
- the plurality of tortuous pathways is circumferentially spaced.
- a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet.
- the pathway inlet is located radially inboard of the pathway outlet.
- a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
- the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
- a shaft is operably connected to the impeller.
- a bearing assembly includes a bearing supportive of the shaft and a bearing support housing into which the bearing assembly is installed.
- the seal support ring is located axially between the impeller and the bearing support housing.
- the deflector ramp deflects the airflow from impacting on the bearing support housing.
- the seal support ring is installed to the bearing support housing.
- an electrical motor is operably connected to the shaft to drive rotation of the impeller about the central axis.
- the sealing element of the impeller is located at a sealing flange of the impeller extending axially from the impeller.
- the compressed airflow is directed from the outlet to a cabin of an aircraft.
- FIG. 1 is a schematic illustration of an embodiment of a cabin air compressor
- FIG. 2 is a perspective view of an embodiment of a labyrinth seal mating ring of a cabin air compressor
- FIG. 3 is a partial cross-sectional view of an embodiment of a labyrinth seal ring installed into a cabin air compressor;
- FIG. 4 is a perspective view of an embodiment of a downstream side of a labyrinth seal ring.
- FIG. 5 is another perspective view of an embodiment of a downstream side of a labyrinth seal ring.
- the cabin air compressor 10 includes a compressor housing 12 in which a compressor impeller 14 is located.
- the compressor impeller 14 is driven by a shaft 16 .
- the shaft 16 is driven by a power source, which in some embodiments is an electric motor 20 .
- Airflow 22 at ambient pressure enters the cabin air compressor 10 at an inlet 18 and is urged across the compressor impeller 14 and compressed.
- the compressed airflow 22 then is directed through an outlet 24 to a selected location, for example, aircraft cabin 26 .
- the shaft 16 and compressor impeller 14 are supported by a bearing 28 , which is installed in a bearing support housing 30 located in the compressor housing 12 .
- a labyrinth seal 32 is located at an impeller outer perimeter 34 to prevent airflow from leaking past the impeller outer perimeter 34 .
- the labyrinth seal 32 is installed in and supported by a labyrinth seal mating ring 36 installed to the bearing support housing 30 .
- this labyrinth seal mating ring 36 includes features to prevent erosion of the bearing support housing 30 .
- the labyrinth seal mating ring 36 is a ring structure, having a ring outer surface 38 , which mates to the bearing support housing 30 . While illustrated as a complete ring, in some embodiments the labyrinth seal mating ring 36 may be a circumferentially segmented structure.
- the labyrinth seal 32 is located at a ring inner surface 42 , substantially opposite to the ring outer surface 38 .
- the labyrinth seal mating ring 36 is formed from a relatively hard material, while the labyrinth seal 32 is formed from a relatively soft material.
- the labyrinth seal 32 when installed, the labyrinth seal 32 is located at a corresponding impeller sealing surface 44 of the compressor impeller 14 .
- the impeller sealing surface 44 is located at a sealing flange 46 extending from a downstream side 48 of the compressor impeller 14 opposite an upstream side 50 relative to the location of the inlet 18 .
- the labyrinth seal 32 and the impeller sealing surface 44 define a seal interface 52 .
- the labyrinth seal mating ring 36 includes a deflector ramp 54 extending radially inboard from the ring inner surface 42 .
- the deflector ramp 54 also extends radially inboard of a radial location of the seal interface 52 .
- the deflector ramp 54 is curvilinear such as shown in FIG. 3 , while in other embodiments, the deflector ramp 54 may be another shape, such as linear or some combination of curvilinear and linear.
- air flow 22 that leaks past the seal interface 52 as leakage airflow 56 is diverted radially inwardly by the deflector ramp 54 , to reduce impact of the leakage airflow 56 and any included particles or foreign objects on a support wall 58 of the bearing support housing 30 .
- Such diversion of the leakage airflow 56 by the deflector ramp 54 reduces erosion of the bearing support housing 30 .
- the leakage airflow 56 typically has a significant tangential or circumferential velocity component due to rotation of the compressor impeller 14 .
- a downstream side 60 of the labyrinth seal mating ring 36 illustrated is a downstream side 60 of the labyrinth seal mating ring 36 .
- the downstream side 60 includes a plurality of tortuous pathways 62 formed into the downstream side 60 .
- the plurality of tortuous pathways 62 are circumferentially spaced along the downstream side 60 , and in some embodiments are equally circumferentially spaced.
- the tortuous pathways 62 each have a pathway inlet 64 and a pathway outlet 66 , and in some embodiments the pathway inlet 64 is located radially inboard of the pathway outlet 66 .
- the tortuous pathway 62 extends between the pathway inlet 64 and the pathway outlet 66 , with in some embodiments an S-shape, a multiple S-shape, a Z-shape, or the like.
- the leakage airflow 56 at the downstream side 60 encounters the tortuous pathways 62 , and at least a portion of the leakage airflow 56 is diverted into the tortuous pathways 62 via the pathway inlets 64 .
- the leakage airflow 56 is slowed and diffused such that the velocity of the leakage airflow 56 is greatly reduced as the leakage airflow 56 exits the tortuous pathways 62 at their respective pathway outlets 66 .
- tortuous pathways 62 thereby reduce the tangential velocity component of the leakage airflow 56 to reduce the erosion of the bearing support housing 30 .
- the labyrinth seal mating ring 36 described herein reduces erosion of the bearing support housing 30 of the cabin air compressor 10 , thus extending the service life of the bearing support housing 30 and the cabin air compressor 10 overall. Further, the labyrinth seal mating ring 36 is configured to be retrofittable into existing cabin air compressors 10 , without the need to modify surrounding components.
Abstract
A compressor assembly includes an impeller rotatable about a central axis and a seal assembly. The seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis. A plurality of tortuous pathways are formed in a downstream surface of the seal support ring and are configured to diffuse a tangential component of the airflow.
Description
- Exemplary embodiments pertain to the art of environmental control units for, for example, aircraft.
- On some aircraft, the cabin and/or other areas are pressurized by an electrically-driven cabin air compressor (CAC). The CAC takes in air flow at atmospheric pressure from outside the aircraft and compresses the airflow to a comfortable pressure for the aircraft cabin. This compressed air flow is then directed into the cabin.
- In some operating conditions, erosion damage occurs to a bearing support housing downstream of the compressor impeller. This erosion damage occurs when foreign object particles bypass a labyrinth seal between the impeller and the bearing support housing and subsequently impact the bearing support housing. Such erosion of the bearing support housing shortens the service life of the bearing support housing specifically and the cabin air compressor in general.
- In one embodiment, a compressor assembly includes an impeller rotatable about a central axis and a seal assembly. The seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis. A plurality of tortuous pathways are formed in a downstream surface of the seal support ring and are configured to diffuse a tangential component of the airflow.
- Additionally or alternatively, in this or other embodiments the plurality of tortuous pathways is circumferentially spaced.
- Additionally or alternatively, in this or other embodiments a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet. The pathway inlet is located radially inboard of the pathway outlet.
- Additionally or alternatively, in this or other embodiments a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
- Additionally or alternatively, in this or other embodiments the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
- Additionally or alternatively, in this or other embodiments a shaft is operably connected to the impeller, and a bearing assembly includes a bearing supportive of the shaft and a bearing support housing into which the bearing assembly is installed. The seal support ring is located axially between the impeller and the bearing support housing.
- Additionally or alternatively, in this or other embodiments the deflector ramp deflects the airflow from impacting on the bearing support housing.
- Additionally or alternatively, in this or other embodiments the seal support ring is installed to the bearing support housing.
- Additionally or alternatively, in this or other embodiments the sealing element of the impeller is located at a sealing flange of the impeller extending axially from the impeller.
- In another embodiment, a cabin air compressor includes a compressor housing having an inlet and an outlet, and an impeller located in the housing. The impeller is rotatable about a central axis and is configured to compress an airflow directed through the inlet and direct the compressed airflow to the outlet. A seal assembly includes a labyrinth seal defining a seal interface with a sealing element of the impeller and a seal support ring into which the labyrinth seal is installed. The seal support includes a deflector ramp fluidly downstream of the seal interface. The deflector ramp is configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis. A plurality of tortuous pathways are formed in a downstream surface of the seal support ring and configured to diffuse a tangential component of the airflow.
- Additionally or alternatively, in this or other embodiments the plurality of tortuous pathways is circumferentially spaced.
- Additionally or alternatively, in this or other embodiments a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet. The pathway inlet is located radially inboard of the pathway outlet.
- Additionally or alternatively, in this or other embodiments a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
- Additionally or alternatively, in this or other embodiments the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
- Additionally or alternatively, in this or other embodiments a shaft is operably connected to the impeller. A bearing assembly includes a bearing supportive of the shaft and a bearing support housing into which the bearing assembly is installed. The seal support ring is located axially between the impeller and the bearing support housing.
- Additionally or alternatively, in this or other embodiments the deflector ramp deflects the airflow from impacting on the bearing support housing.
- Additionally or alternatively, in this or other embodiments the seal support ring is installed to the bearing support housing.
- Additionally or alternatively, in this or other embodiments an electrical motor is operably connected to the shaft to drive rotation of the impeller about the central axis.
- Additionally or alternatively, in this or other embodiments the sealing element of the impeller is located at a sealing flange of the impeller extending axially from the impeller.
- Additionally or alternatively, in this or other embodiments the compressed airflow is directed from the outlet to a cabin of an aircraft.
- The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike:
-
FIG. 1 is a schematic illustration of an embodiment of a cabin air compressor; -
FIG. 2 is a perspective view of an embodiment of a labyrinth seal mating ring of a cabin air compressor; -
FIG. 3 is a partial cross-sectional view of an embodiment of a labyrinth seal ring installed into a cabin air compressor; -
FIG. 4 is a perspective view of an embodiment of a downstream side of a labyrinth seal ring; and -
FIG. 5 is another perspective view of an embodiment of a downstream side of a labyrinth seal ring. - 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.
- Referring now to
FIG. 1 , illustrated is a schematic illustration of an embodiment of acabin air compressor 10. Thecabin air compressor 10 includes acompressor housing 12 in which acompressor impeller 14 is located. Thecompressor impeller 14 is driven by ashaft 16. Theshaft 16, in turn, is driven by a power source, which in some embodiments is anelectric motor 20.Airflow 22 at ambient pressure enters thecabin air compressor 10 at aninlet 18 and is urged across thecompressor impeller 14 and compressed. Thecompressed airflow 22 then is directed through anoutlet 24 to a selected location, for example,aircraft cabin 26. Theshaft 16 andcompressor impeller 14 are supported by abearing 28, which is installed in abearing support housing 30 located in thecompressor housing 12. Alabyrinth seal 32 is located at an impellerouter perimeter 34 to prevent airflow from leaking past the impellerouter perimeter 34. Thelabyrinth seal 32 is installed in and supported by a labyrinthseal mating ring 36 installed to thebearing support housing 30. As will be discussed in greater detail below, this labyrinthseal mating ring 36 includes features to prevent erosion of thebearing support housing 30. - Referring now to
FIG. 2 , the labyrinthseal mating ring 36 is shown in more detail. The labyrinthseal mating ring 36 is a ring structure, having a ringouter surface 38, which mates to thebearing support housing 30. While illustrated as a complete ring, in some embodiments the labyrinthseal mating ring 36 may be a circumferentially segmented structure. Thelabyrinth seal 32 is located at a ringinner surface 42, substantially opposite to the ringouter surface 38. In some embodiments, the labyrinthseal mating ring 36 is formed from a relatively hard material, while thelabyrinth seal 32 is formed from a relatively soft material. - Referring now to
FIG. 3 , when installed, thelabyrinth seal 32 is located at a correspondingimpeller sealing surface 44 of thecompressor impeller 14. In some embodiments, theimpeller sealing surface 44 is located at a sealingflange 46 extending from adownstream side 48 of thecompressor impeller 14 opposite anupstream side 50 relative to the location of theinlet 18. Thelabyrinth seal 32 and theimpeller sealing surface 44 define aseal interface 52. The labyrinthseal mating ring 36 includes adeflector ramp 54 extending radially inboard from the ringinner surface 42. Thedeflector ramp 54 also extends radially inboard of a radial location of theseal interface 52. In some embodiments, thedeflector ramp 54 is curvilinear such as shown inFIG. 3 , while in other embodiments, thedeflector ramp 54 may be another shape, such as linear or some combination of curvilinear and linear. - In operation,
air flow 22 that leaks past theseal interface 52 asleakage airflow 56 is diverted radially inwardly by thedeflector ramp 54, to reduce impact of theleakage airflow 56 and any included particles or foreign objects on asupport wall 58 of thebearing support housing 30. Such diversion of theleakage airflow 56 by thedeflector ramp 54 reduces erosion of thebearing support housing 30. - The
leakage airflow 56 typically has a significant tangential or circumferential velocity component due to rotation of thecompressor impeller 14. Referring now toFIG. 4 andFIG. 5 , illustrated is adownstream side 60 of the labyrinthseal mating ring 36. Thedownstream side 60 includes a plurality oftortuous pathways 62 formed into thedownstream side 60. The plurality oftortuous pathways 62 are circumferentially spaced along thedownstream side 60, and in some embodiments are equally circumferentially spaced. Thetortuous pathways 62 each have apathway inlet 64 and apathway outlet 66, and in some embodiments thepathway inlet 64 is located radially inboard of thepathway outlet 66. Thetortuous pathway 62 extends between thepathway inlet 64 and thepathway outlet 66, with in some embodiments an S-shape, a multiple S-shape, a Z-shape, or the like. - In operation, the
leakage airflow 56 at thedownstream side 60 encounters thetortuous pathways 62, and at least a portion of theleakage airflow 56 is diverted into thetortuous pathways 62 via thepathway inlets 64. Along thetortuous pathway 62, theleakage airflow 56 is slowed and diffused such that the velocity of theleakage airflow 56 is greatly reduced as theleakage airflow 56 exits thetortuous pathways 62 at theirrespective pathway outlets 66. - The
tortuous pathways 62 thereby reduce the tangential velocity component of theleakage airflow 56 to reduce the erosion of thebearing support housing 30. - The labyrinth
seal mating ring 36 described herein reduces erosion of thebearing support housing 30 of thecabin air compressor 10, thus extending the service life of thebearing support housing 30 and thecabin air compressor 10 overall. Further, the labyrinthseal mating ring 36 is configured to be retrofittable into existingcabin air compressors 10, without the need to modify surrounding components. - 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.
Claims (20)
1. A compressor assembly, comprising:
an impeller rotatable about a central axis; and
a seal assembly including:
a labyrinth seal defining a seal interface with a sealing element of the impeller;
a seal support ring into which the labyrinth seal is installed, the seal support including a deflector ramp fluidly downstream of the seal interface, the deflector ramp configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis; and
a plurality of tortuous pathways formed in a downstream surface of the seal support ring and configured to diffuse a tangential component of the airflow.
2. The compressor assembly of claim 1 , wherein the plurality of tortuous pathways is circumferentially spaced.
3. The compressor assembly of claim 1 , wherein a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet, the pathway inlet disposed radially inboard of the pathway outlet.
4. The compressor inlet of claim 1 , wherein a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
5. The compressor assembly of claim 1 , wherein the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
6. The compressor assembly of claim 1 , further comprising:
a shaft operably connected to the impeller; and
a bearing assembly including:
a bearing supportive of the shaft; and
a bearing support housing into which the bearing assembly is installed, the seal support ring disposed axially between the impeller and the bearing support housing.
7. The compressor assembly of claim 6 , wherein the deflector ramp deflects the airflow from impacting on the bearing support housing.
8. The compressor assembly of claim 6 , wherein the seal support ring is installed to the bearing support housing.
9. The compressor assembly of claim 1 , wherein the sealing element of the impeller is disposed at a sealing flange of the impeller extending axially from the impeller.
10. A cabin air compressor, comprising:
a compressor housing having an inlet and an outlet;
an impeller disposed in the housing, the impeller rotatable about a central axis and configured to compress an airflow directed through the inlet and direct the compressed airflow to the outlet; and
a seal assembly including:
a labyrinth seal defining a seal interface with a sealing element of the impeller;
a seal support ring into which the labyrinth seal is installed, the seal support including a deflector ramp fluidly downstream of the seal interface, the deflector ramp configured to turn an airflow leaking through the seal interface radially inwardly toward the central axis; and
a plurality of tortuous pathways formed in a downstream surface of the seal support ring and configured to diffuse a tangential component of the airflow.
11. The cabin air compressor of claim 10 , wherein the plurality of tortuous pathways is circumferentially spaced.
12. The cabin air compressor of claim 10 , wherein a tortuous pathway of the plurality of tortuous pathways includes a pathway inlet and a pathway outlet, the pathway inlet disposed radially inboard of the pathway outlet.
13. The cabin air compressor of claim 10 , wherein a tortuous pathway of the plurality of tortuous pathways is one of S-shaped, multiple S-shaped or Z-shaped.
14. The cabin air compressor of claim 10 , wherein the labyrinth seal is formed from a first, relatively soft material and the seal support ring is formed from a second, relatively hard material.
15. The cabin air compressor of claim 10 , further comprising:
a shaft operably connected to the impeller; and
a bearing assembly including:
a bearing supportive of the shaft; and
a bearing support housing into which the bearing assembly is installed, the seal support ring disposed axially between the impeller and the bearing support housing.
16. The cabin air compressor of claim 15 , wherein the deflector ramp deflects the airflow from impacting on the bearing support housing.
17. The cabin air compressor of claim 15 , wherein the seal support ring is installed to the bearing support housing.
18. The cabin air compressor of claim 15 , further comprising an electrical motor operably connected to the shaft to drive rotation of the impeller about the central axis.
19. The cabin air compressor of claim 10 , wherein the sealing element of the impeller is disposed at a sealing flange of the impeller extending axially from the impeller.
20. The cabin air compressor of claim 10 , wherein the compressed airflow is directed from the outlet to a cabin of an aircraft.
Priority Applications (2)
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US17/176,606 US11408299B1 (en) | 2021-02-16 | 2021-02-16 | Erosion mitigating labyrinth seal mating ring |
EP22156825.6A EP4043736A1 (en) | 2021-02-16 | 2022-02-15 | Erosion mitigating labyrinth seal mating ring |
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US17/176,606 US11408299B1 (en) | 2021-02-16 | 2021-02-16 | Erosion mitigating labyrinth seal mating ring |
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US20220259981A1 true US20220259981A1 (en) | 2022-08-18 |
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US11408299B1 (en) | 2022-08-09 |
EP4043736A1 (en) | 2022-08-17 |
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