US20150233386A1 - First stage turbine housing for an air cycle machine - Google Patents

First stage turbine housing for an air cycle machine Download PDF

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Publication number
US20150233386A1
US20150233386A1 US14/180,777 US201414180777A US2015233386A1 US 20150233386 A1 US20150233386 A1 US 20150233386A1 US 201414180777 A US201414180777 A US 201414180777A US 2015233386 A1 US2015233386 A1 US 2015233386A1
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United States
Prior art keywords
housing
radius
ratio
central axis
shaft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/180,777
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English (en)
Inventor
Craig M. Beers
Seth E. Rosen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Priority to US14/180,777 priority Critical patent/US20150233386A1/en
Assigned to HAMILTON SUNDSTRAND CORPORATION reassignment HAMILTON SUNDSTRAND CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BEERS, CRAIG M., ROSEN, SETH E.
Priority to CN201410852561.4A priority patent/CN104847422A/zh
Publication of US20150233386A1 publication Critical patent/US20150233386A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
    • 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
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • 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
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps

Definitions

  • ACMs Air Cycle Machines
  • ACMs may be used to compress air in a compressor section.
  • the compressed air is discharged to a downstream heat exchanger and further routed to a turbine.
  • the turbine extracts energy from the expanded air to drive the compressor.
  • the air output from the turbine may be utilized as an air supply for a vehicle, such as the cabin of an aircraft.
  • ACMs may be used to achieve a desired pressure, temperature, and humidity in the air that is transferred to the environmental control system of the aircraft.
  • ACMs often have a three-wheel or four-wheel configuration.
  • a turbine drives both a compressor and a fan which rotate on a common shaft.
  • two turbine sections drive a compressor and a fan on a common shaft.
  • Airflow from one working fluid must be directed through a ram circuit consisting of a heat exchanger and the fan section of the ACM. Airflow from a second working fluid must be directed into the compressor section, away from the compressor section towards the heat exchanger, from the heat exchanger to the turbine or turbines, and from the final turbine stage out of the ACM. In at least some of these transfers, it is desirable to direct air radially with respect to the central axis of the ACM. To accomplish this, rotating nozzles may be used to generate radial in-flow and/or out-flow.
  • ACMs often have more than one housing section.
  • the housings used in an ACM are used to contain airflow routed through the ACM, as well as rotating parts.
  • housing components are configured adjacent to seals and/or other housing components to achieve airflow containment.
  • a housing of an air cycle machine includes a static seal portion, a main bore housing portion, a shroud pilot housing portion, and a thrust plate housing portion.
  • the static seal portion is arranged about a central axis and defines static seal radius D 1 .
  • the main bore housing portion is arranged about the central axis and circumscribes the shaft arranged along the central axis.
  • the main bore housing defines central bore inner radius D 2 .
  • the shroud pilot housing radius is arranged about the central axis and defines shroud pilot radius D 3 .
  • the thrust plate housing portion is arranged about the central axis and defines insulator seal plate radius D 4 .
  • a ratio D 1 /D 2 is 0.8394 to 0.8416
  • a ratio D 1 /D 3 is 0.4315 to 0.4322
  • a ratio D 1 /D 4 is 0.2517 to 0.2521
  • a ratio D 2 /D 3 is 0.5130 to 0.5146
  • a ratio D 2 /D 4 is 0.2993-0.3001
  • a ratio D 3 /D 4 is 0.5828-0.5838.
  • An air cycle machine includes a fan section arranged around a shaft.
  • the fan section is capable of routing a first working fluid.
  • a compressor section is arranged next to the fan section and positioned around the shaft and is capable of compressing a second working fluid.
  • a turbine section is arranged next to the compressor section and positioned around the shaft. The turbine section is capable of converting potential energy of the second working fluid into rotational energy.
  • a heat exchanger is capable of exchanging heat between the first working fluid and the second working fluid.
  • a housing of an air cycle machine includes a static seal portion, a main bore housing portion, a shroud pilot housing portion, and a thrust plate housing portion. The static seal portion is arranged about a central axis and defines static seal radius D 1 .
  • the main bore housing portion is arranged about the central axis and circumscribes the shaft arranged along the central axis.
  • the main bore housing defines central bore inner radius D 2 .
  • the shroud pilot housing radius is arranged about the central axis and defines shroud pilot radius D 3 .
  • the thrust plate housing portion is arranged about the central axis and defines insulator seal plate radius D 4 .
  • a ratio D 1 /D 2 is 0.8394 to 0.8416
  • a ratio D 1 /D 3 is 0.4315 to 0.4322
  • a ratio D 1 /D 4 is 0.2517 to 0.2521
  • a ratio D 2 /D 3 is 0.5130 to 0.5146
  • a ratio D 2 /D 4 is 0.2993-0.3001
  • a ratio D 3 /D 4 is 0.5828-0.5838.
  • FIG. 1 is a cross-sectional view of an air cycle machine.
  • FIG. 2 is a perspective view of a housing of the air cycle machine.
  • the dimensions of an air cycle machine housing are selected in order to achieve several goals. Reduced drag of rotating shaft on static shaft seal minimizes friction losses and transfers more turbine power to the compressor and fan. Seal clearance is desirably minimized, in order to minimize compressor inlet flow lost through the seal. Shaft excursions, such as seals, result in intimate contact between shaft seal teeth and associated seal lands. The seal clearance losses are balanced against the frictional losses of seal drag during shaft excursions. Clearance is maintained between the rotating shaft teeth and the seal land to reduce or eliminate sub-synchronous vibrations in foil bearings of the air cycle machine. Further, the leakage from excursions such as seals is prevented from dumping into part of the bearing cooling flow path. Excessive leakage into this flowpath could result in a blockage of cooling flow. Seal sizing prevents the excessive leakage that could cause reduced bearing cooling flow and over-temperature of the bearing surfaces.
  • Optimizing performance of a compressor and a turbine can be quite different.
  • the inlet air is at a lower pressure than the outlet air, but the opposite is true for a turbine.
  • the compressor inlet air contains a high temperature, and the compressor discharge temperature is even greater.
  • the turbine the inlet air is at a cool temperature and the outlet is at an even colder temperature.
  • different methodologies are required for the turbine and compressor. If the turbine were designed using an the incorrect optimization technique, either the clearance would be too loose and cause poor turbine performance or the seal clearance would be too tight and cause a side loading of the foil bearings. In the specific instance of the seal clearance being too tight, the foil bearings would be excessively side loaded and result in poor reliability or reduced load capability.
  • One feature of this ACM is the use of the bearing clearances and seal sizes to prevent excessively side-loading the bearings without having any negative impact on turbine performance or additional bearing cooling.
  • FIG. 1 is a cross-sectional view of ACM 2 , which is a four-wheel ACM.
  • ACM 2 includes fan section 4 , compressor section 6 , first stage turbine section 8 , and second stage turbine section 10 , which are all connected to shaft 12 .
  • Shaft 12 rotates about central axis 14 .
  • Fan section 4 , compressor section 6 , first stage turbine section 8 , and second stage turbine section 10 are also connected to one another via shaft 12 .
  • Shaft 12 runs along central axis 14 , and is connected to at least compressor nozzle 26 , first stage turbine nozzle 32 , and second stage turbine nozzle 38 .
  • Fan blades 20 may also be connected to shaft 12 .
  • working fluid When working fluid passes through ACM 2 , it is first compressed in compressor section 6 , and then expanded in first stage turbine section 8 and second stage turbine section 10 . Often, a first working fluid is heated or cooled in a heat exchanger (not shown) through which working fluid is routed as it passes between compressor section 6 and first stage turbine section 8 . First stage turbine section 8 and second stage turbine section 10 extract energy from the working fluid, turning shaft 12 about central axis 14 . Meanwhile, a second working fluid is routed through the same heat exchanger by fan section 4 .
  • the first working fluid may be routed from a bleed valve of a gas turbine engine through compressor section 6 , to a heat exchanger, to first stage turbine section 8 , then to second stage turbine section 10 , and then to the environmental control system of an aircraft.
  • the second working fluid may be ram air that is pulled by fan section 4 through the same heat exchanger to cool the first working fluid to a desired temperature before routing of the first working fluid to the turbine sections 8 and 10 .
  • the output provided at the second stage turbine 10 may be adjusted to a desired temperature, pressure, and/or relative humidity.
  • Fan section 4 includes fan inlet 16 and fan outlet 18 .
  • Fan inlet 16 is an opening in ACM 2 that receives working fluid from another source, such as a ram air scoop.
  • Fan outlet 18 allows working fluid to escape fan section 4 .
  • Fan blades 20 may be used to draw working fluid into fan section 4 .
  • Compressor section 6 includes compressor inlet 22 , compressor outlet 24 , compressor nozzle 26 , and compressor blades 27 .
  • Compressor inlet 22 is a duct defining an aperture through which working fluid to be compressed is received from another source.
  • Compressor outlet 24 allows working fluid to be routed to other systems after it has been compressed.
  • Compressor nozzle 26 is a nozzle section that rotates through working fluid in compressor section 6 .
  • Compressor nozzle 26 directs working fluid from compressor inlet 22 to compressor outlet 24 via compressor blades 27 .
  • Compressor nozzle 26 is a radial out-flow rotor.
  • First stage turbine section 8 includes first stage turbine inlet 28 , first stage turbine outlet 30 , first stage turbine nozzle 32 , and first stage turbine blades 33 .
  • First stage turbine inlet 28 is a duct defining an aperture through which working fluid passes prior to expansion in first stage turbine section 8 .
  • First stage turbine outlet 30 is a duct defining an aperture through which working fluid (which has expanded) departs first stage turbine section 8 .
  • First stage turbine nozzle 32 is a nozzle section that rotates through working fluid in first stage turbine section 8 .
  • First stage turbine nozzle 32 cooperates with first stage turbine blades 33 to extract energy from working fluid passing therethrough, driving the rotation of first stage turbine section 8 and attached components, including shaft 12 , fan section 4 , and compressor section 6 .
  • First stage turbine nozzle 32 is a radial in-flow rotor.
  • Second stage turbine section 10 includes second stage turbine inlet 34 , second stage turbine outlet 36 , second stage turbine nozzle 38 , and second stage turbine blades 39 .
  • Second stage turbine inlet 34 is a duct defining an aperture through which working fluid passes prior to expansion in second stage turbine section 10 .
  • Second stage turbine outlet 36 is a duct defining an aperture through which working fluid (which has expanded) departs second stage turbine section 10 .
  • Second stage turbine nozzle 38 is a nozzle section that cooperates with second stage turbine blades 39 to extract energy from working fluid passing therethrough, driving the rotation of second stage turbine section 10 and attached components, including shaft 12 , fan section 4 , and compressor section 6 .
  • second stage turbine nozzle 38 is a radial out-flow rotor.
  • Working fluid passes from second stage turbine inlet 34 to cavity 35 , where it is incident upon second stage turbine nozzle 38 .
  • Working fluid then passes between nozzle blades (not shown).
  • Turbine nozzle 38 is stationary, and the nozzle vanes guide the flow for optimum entry into the turbine rotor. The flow of causes turbine blades 39 to rotate and turn shaft 12 .
  • Shaft 12 is a rod, such as a titanium tie-rod, used to connect other components of ACM 2 .
  • Shaft 12 includes a seal portion arranged partway along its length.
  • Central axis 14 is an axis with respect to which other components may be arranged.
  • Fan section 4 is connected to compressor section 6 .
  • fan outlet 18 is coupled to compressor inlet 22 .
  • Working fluid is drawn through fan inlet 16 and discharged through fan outlet 18 by fan blades 20 .
  • Working fluid from fan outlet 18 is routed to compressor inlet 22 for compression in compressor section 6 .
  • compressor section 6 is coupled with first stage turbine section 8 .
  • Working fluid from compressor outlet 24 is routed to first stage turbine inlet 28 .
  • Fan section 4 and compressor section 6 share housing 40 .
  • Housing 40 encloses the moving parts and air paths through fan section 4 and compressor section 6 .
  • the size and geometry of housing 40 define the flow of air through ACM 2 .
  • housing 40 is arranged about shaft 12 so as to prevent excessive airflow around shaft 12 .
  • a static seal portion is included in shaft 12 , directly adjacent to static seal portion 44 .
  • the outer radius of the seal portion is set such that a seal is formed with static seal portion 44 of housing 40 .
  • the outer radius of shaft 12 at the static seal portion is equal to or slightly less than static seal radius D 1 .
  • Housing 40 has specific dimensions to coordinate with adjacent housing sections, such as the housing surrounding turbine section 8 .
  • Housing 40 includes main bore housing portion 42 , static seal portion 44 , shroud pilot housing 46 , and thrust plate 48 .
  • Static seal portion 44 is the portion of housing 40 that circumscribes shaft 12 at the longitudinal are at which shaft 12 includes a seal. In this way, static seal portion 44 prevents flow of fluid between housing 40 and shaft 12 .
  • the radius of housing 40 from central axis 14 to static seal portion 44 is illustrated as static seal radius D 1 .
  • Static seal radius D 1 is between 2.0724 cm and 2.07365 cm (0.8159 in. and 0.8164 in.).
  • Main bore housing portion 42 is the portion of housing 40 that circumscribes shaft 12 so as to prevent excessive airflow around shaft 12 .
  • the radius of housing 40 from central axis 14 to main bore housing portion 42 is illustrated as central bore inner radius D 2 .
  • Central bore inner radius D 2 is between 2.4638 cm and 2.4689 cm (0.9700 in. and 0.9720 in.).
  • Shroud pilot housing 46 defines a portion of housing 40 at the point where the radial distance between central axis 14 and housing 40 is at a local minimum.
  • Shroud pilot housing portion 46 is configured to mate with a complimentary feature, turbine housing 50 .
  • turbine housing 50 By coupling with turbine housing 50 , shroud pilot housing 46 prevents working fluid passing through the compressor inlet 22 from intermixing with compressed fluid at the compressor outlet 24 .
  • the radius of housing 40 from central axis 14 to shroud pilot housing 46 is illustrated as shroud pilot housing radius D 3 .
  • Shroud pilot housing radius D 3 is between 4.79805 cm and 4.80315 cm (1.8890 in. and 1.8910 in.).
  • Thrust plate 48 is a portion of housing 40 that extends between first stage turbine section 8 and second stage turbine section 10 . Thrust plate 48 separates second stage turbine inlet 34 and cavity 35 . The radius from central axis 14 to thrust plate 48 is illustrated as thrust plate radius D 4 . Thrust plate housing radius D 4 is between 8.22705 cm and 8.23215 cm (3.2390 in. and 3.2410 in.).
  • the ratios between static seal radius D 1 , central bore inner radius D 2 , shroud pilot housing radius D 3 , and thrust plate housing radius D 4 can also be set to reach optimized bearing cooling and seal leakage throughout ACM 2 . Optimized clearance of seals in ACM 2 also permits proper operation of the shaft/rotor system.
  • D 1 /D 2 is 0.8394 to 0.8416
  • a ratio D 1 /D 3 is 0.4315 to 0.4322
  • a ratio D 1 /D 4 is 0.2517 to 0.2521
  • a ratio D 2 /D 3 is 0.5130 to 0.5146
  • a ratio D 2 /D 4 is 0.2993-0.3001
  • a ratio D 3 /D 4 is 0.5828-0.5838
  • FIG. 2 is a perspective view of housing 40 , illustrating static seal radius D 1 , central bore inner radius D 2 , shroud pilot housing radius D 3 , and thrust plate radius D 4 .
  • Components of ACM 2 of FIG. 1 including the adjacent housing of turbine section 8 and shaft 12 , have been removed to more clearly illustrate the specific dimensions of housing 40 .
  • a static seal portion D 1 , main bore housing radius D 2 , shroud pilot housing radius D 3 , and thrust plate housing radius D 4 have specific ranges of dimensions that are optimal.
  • a housing of an air cycle machine may include a static seal portion arranged about a central axis and configured to circumscribe a static seal defined by a shaft arranged along the central axis.
  • the static seal portion defines a static seal radius D 1 .
  • a main bore housing portion is arranged about the central axis and positioned longitudinally adjacent to the static seal portion.
  • the main bore housing is configured to circumscribe the shaft.
  • the main bore housing defines a central bore inner radius D 2 .
  • a shroud pilot housing portion is arranged about the central axis.
  • the shroud pilot housing portion defines a shroud pilot radius D 3 .
  • a thrust plate housing portion is arranged about the central axis and is configured to mate with an adjacent turbine section component.
  • the thrust plate housing portion defining an insulator seal plate radius D 4 .
  • the ratios as between D 1 , D 2 , D 3 , and D 4 include D 1 /D 2 between 0.8394 to 0.8416, D 1 /D 3 between 0.4315 to 0.4322, D 1 /D 4 between 0.2517 to 0.2521, D 2 /D 3 between 0.5130 to 0.5146, D 2 /D 4 between 0.2993-0.3001, and D 3 /D 4 between 0.5828-0.5838.
  • the housing of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations, and/or additional components.
  • the static seal radius may be between 2.0724 cm and 2.07365 cm.
  • the main bore housing radius may be between 2.4638 cm and 2.4689 cm.
  • the shroud pilot housing radius may be between 4.79805 cm and 4.80315 cm.
  • the thrust plate housing radius may be between 8.22705 cm and 8.23215 cm.
  • the turbine section component may be a turbine section housing.
  • the turbine section component may be a first stage turbine section housing.
  • the shroud housing pilot portion may be configured to mate with the adjacent turbine section component.
  • An air cycle machine may include a shaft.
  • the air cycle machine may further include a fan section arranged around a portion of the shaft.
  • the fan section is capable of routing a first working fluid.
  • the air cycle machine includes a compressor section arranged adjacent to the fan section and positioned around the shaft.
  • the compressor section is capable of compressing a second working fluid.
  • the turbine section is arranged adjacent to the compressor section and positioned around the shaft.
  • the turbine section is capable of converting potential energy of the second working fluid to rotational energy.
  • a heat exchanger is capable of exchanging heat between the first working fluid and the second working fluid.
  • a housing forms a part of both the fan section and the compressor section.
  • the housing includes a static seal portion arranged about a central axis and configured to circumscribe a static seal defined by a shaft arranged along the central axis.
  • the static seal portion defines a static seal radius D 1 .
  • a main bore housing portion is arranged about the central axis and positioned longitudinally adjacent to the static seal portion.
  • the main bore housing is configured to circumscribe the shaft.
  • the main bore housing defines a central bore inner radius D 2 .
  • a shroud pilot housing portion is arranged about the central axis.
  • the shroud pilot housing portion defines a shroud pilot radius D 3 .
  • a thrust plate housing portion is arranged about the central axis and is configured to mate with an adjacent turbine section component.
  • the thrust plate housing portion defining an insulator seal plate radius D 4 .
  • the ratios as between D 1 , D 2 , D 3 , and D 4 include D 1 /D 2 between 0.8394 to 0.8416, D 1 /D 3 between 0.4315 to 0.4322, D 1 /D 4 between 0.2517 to 0.2521, D 2 /D 3 between 0.5130 to 0.5146, D 2 /D 4 between 0.2993-0.3001, and D 3 /D 4 between 0.5828-0.5838.
  • the housing of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations, and/or additional components.
  • the second working fluid may pass through the heat exchanger located between the compressor section and the turbine section.
  • the fan section, the compressor section, and the turbine section may be connected by the shaft to form a single spool.
  • the static seal radius may be between 0.8159 in. and 0.8164 in.
  • the main bore housing radius may be between 0.9700 in. and 0.9720 in.
  • the shroud pilot housing radius may be between 1.8890 in. and 1.8910 in.
  • the thrust plate housing radius may be between 3.2390 in. and 3.2410 in.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/180,777 2014-02-14 2014-02-14 First stage turbine housing for an air cycle machine Abandoned US20150233386A1 (en)

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Application Number Priority Date Filing Date Title
US14/180,777 US20150233386A1 (en) 2014-02-14 2014-02-14 First stage turbine housing for an air cycle machine
CN201410852561.4A CN104847422A (zh) 2014-02-14 2014-12-31 空气循环机的第一级涡轮机壳体

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Application Number Priority Date Filing Date Title
US14/180,777 US20150233386A1 (en) 2014-02-14 2014-02-14 First stage turbine housing for an air cycle machine

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190211842A1 (en) * 2018-01-05 2019-07-11 Hamilton Sundstrand Corporation Fan and compressor housing for an air cycle machine
US10619650B2 (en) 2016-05-06 2020-04-14 Hamilton Sundstrand Corporation Air cycle machine fan and compressor housing
US10633099B2 (en) 2018-03-12 2020-04-28 Hamilton Sundstrand Corporation Non-horizontal water extractor
US10661906B2 (en) 2014-09-23 2020-05-26 Hamilton Sundstrand Corporation Fan and compressor housing for an air cycle machine
US11125243B2 (en) 2020-01-02 2021-09-21 Hamilton Sundstrand Corporation Two-wheel air cycle machine
US11655039B2 (en) 2020-04-03 2023-05-23 Hamilton Sundstrand Corporation Turbine housing for a two wheel air cycle machine
US11761349B2 (en) 2020-04-03 2023-09-19 Hamilton Sundstrand Corporation Bearing housing for a two-wheel air cycle machine

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US5309735A (en) * 1991-09-11 1994-05-10 United Technologies Corporation Four wheel air cycle machine
US5311749A (en) * 1992-04-03 1994-05-17 United Technologies Corporation Turbine bypass working fluid admission
US20070134105A1 (en) * 2005-12-14 2007-06-14 Hamilton Sundstrand ACM cooling flow path and thrust load design
US20120156014A1 (en) * 2010-12-21 2012-06-21 Beers Craig M Air cycle machine bearing cooling inlet plate
US20120156011A1 (en) * 2010-12-21 2012-06-21 Richardson Victoria S Air cycle machine seal land
US20130071239A1 (en) * 2011-09-19 2013-03-21 Craig M. Beers Turbine nozzle for air cycle machine
US20140186161A1 (en) * 2012-12-28 2014-07-03 Hamilton Sundstrand Corporation Seal plate
US9103568B2 (en) * 2013-08-02 2015-08-11 Hamilton Sundstrand Corporation Compressor housing for an air cycle machine

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US4507939A (en) * 1983-12-16 1985-04-02 The Garrett Corporation Three wheel center fan cooling turbine apparatus and associated methods
US5224842A (en) * 1992-01-10 1993-07-06 Dziorny Paul J Air cycle machine with interstage venting
US5249934A (en) * 1992-01-10 1993-10-05 United Technologies Corporation Air cycle machine with heat isolation having back-to-back turbine and compressor rotors
US8596967B2 (en) * 2010-12-21 2013-12-03 Hamilton Sundstrand Corporation Turbine shroud for air cycle machine
US8784053B2 (en) * 2010-12-21 2014-07-22 Hamilton Sundstrand Corporation Fan shield and bearing housing for air cycle machine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5309735A (en) * 1991-09-11 1994-05-10 United Technologies Corporation Four wheel air cycle machine
US5311749A (en) * 1992-04-03 1994-05-17 United Technologies Corporation Turbine bypass working fluid admission
US20070134105A1 (en) * 2005-12-14 2007-06-14 Hamilton Sundstrand ACM cooling flow path and thrust load design
US20120156014A1 (en) * 2010-12-21 2012-06-21 Beers Craig M Air cycle machine bearing cooling inlet plate
US20120156011A1 (en) * 2010-12-21 2012-06-21 Richardson Victoria S Air cycle machine seal land
US20130071239A1 (en) * 2011-09-19 2013-03-21 Craig M. Beers Turbine nozzle for air cycle machine
US20140186161A1 (en) * 2012-12-28 2014-07-03 Hamilton Sundstrand Corporation Seal plate
US9103568B2 (en) * 2013-08-02 2015-08-11 Hamilton Sundstrand Corporation Compressor housing for an air cycle machine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10661906B2 (en) 2014-09-23 2020-05-26 Hamilton Sundstrand Corporation Fan and compressor housing for an air cycle machine
US10619650B2 (en) 2016-05-06 2020-04-14 Hamilton Sundstrand Corporation Air cycle machine fan and compressor housing
US20190211842A1 (en) * 2018-01-05 2019-07-11 Hamilton Sundstrand Corporation Fan and compressor housing for an air cycle machine
US10788046B2 (en) * 2018-01-05 2020-09-29 Hamilton Sundstrand Corporation Fan and compressor housing for an air cycle machine
US10633099B2 (en) 2018-03-12 2020-04-28 Hamilton Sundstrand Corporation Non-horizontal water extractor
US11125243B2 (en) 2020-01-02 2021-09-21 Hamilton Sundstrand Corporation Two-wheel air cycle machine
US11655039B2 (en) 2020-04-03 2023-05-23 Hamilton Sundstrand Corporation Turbine housing for a two wheel air cycle machine
US11761349B2 (en) 2020-04-03 2023-09-19 Hamilton Sundstrand Corporation Bearing housing for a two-wheel air cycle machine

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CN104847422A (zh) 2015-08-19

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