US20140026993A1 - Cabin air compressor heat housing - Google Patents

Cabin air compressor heat housing Download PDF

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Publication number
US20140026993A1
US20140026993A1 US13/561,368 US201213561368A US2014026993A1 US 20140026993 A1 US20140026993 A1 US 20140026993A1 US 201213561368 A US201213561368 A US 201213561368A US 2014026993 A1 US2014026993 A1 US 2014026993A1
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United States
Prior art keywords
cabin air
air compressor
heat
diameter
housing
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
US13/561,368
Inventor
Seth E. Rosen
Danielle Mansfield-Marcoux
Brent J. Merritt
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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 US13/561,368 priority Critical patent/US20140026993A1/en
Assigned to HAMILTON SUNDSTRAND CORPORATION reassignment HAMILTON SUNDSTRAND CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MANSFIELD-MARCOUX, DANIELLE, MERRITT, BRENT J., ROSEN, SETH E.
Priority to CN201310321597.5A priority patent/CN103573705B/en
Publication of US20140026993A1 publication Critical patent/US20140026993A1/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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially 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
    • 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
    • F04D29/083—Sealings 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
    • F04D29/40—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
    • F04D29/40—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
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/85978—With pump

Definitions

  • the subject matter disclosed herein relates to aircraft environmental control. More specifically, the subject disclosure relates to a heat housing of a cabin air compressor for an aircraft environmental control system.
  • Environmental control systems are utilized on various types of aircraft for several purposes, such as in cooling systems for the aircraft.
  • components of an ECS may be utilized to remove heat from various aircraft lubrication and electrical systems and/or used to condition aircraft cabin air.
  • a cabin air conditioner includes one or more cabin air compressors (CACs) which compress air entering the system, from an outside source or from a ram air system. The compressed air is delivered to an environmental control system to bring it to a desired temperature and delivered to the aircraft cabin. After passing through the cabin, the air is typically exhausted to the outside.
  • CACs cabin air compressors
  • a cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing.
  • the cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet.
  • the cabin air compressor heat housing further includes a diffuser actuator interface formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
  • a cabin air compressor assembly includes a cabin air compressor heat housing coupled to a cabin air compressor housing.
  • the cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing.
  • the cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet.
  • the cabin air compressor heat housing further includes a diffuser actuator interface formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
  • a method of installing a cabin air compressor heat housing in a cabin air compressor assembly includes coupling a cabin air compressor heat housing to a cabin air compressor housing of the cabin air compressor assembly.
  • the cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing.
  • the cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet.
  • the cabin air compressor heat housing further includes a diffuser actuator interface having a seal groove formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
  • the method also includes inserting a sealing member into the seal groove of the diffuser actuator interface.
  • a diffuser actuator is coupled to the diffuser actuator interface. The sealing member is compressed in the seal groove between the diffuser actuator interface and the diffuser actuator.
  • FIG. 1 is a partial cross-sectional view of a cabin air compressor assembly
  • FIG. 2 is a perspective view of a cabin air compressor heat housing
  • FIG. 3 is a top view of the cabin air compressor heat housing of FIG. 2 ;
  • FIG. 4 is a partial cross-sectional view of the cabin air compressor heat housing of FIG. 3 ;
  • FIG. 5 is a detailed view of a portion of the partial cross-sectional view of the cabin air compressor heat housing of FIG. 4 .
  • FIG. 1 Shown in FIG. 1 is a cross-sectional view of a cabin air compressor (CAC) assembly 12 , one or more of which may be used in an environmental control system 100 for an aircraft.
  • the CAC assembly 12 compresses air flow 14 received at a compressor inlet 16 .
  • the CAC assembly 12 is driven by a CAC motor 28 operably connected to the CAC assembly 12 via a CAC shaft 30 .
  • the CAC motor 28 is an electric motor having a rotor 32 rotatably located at the CAC shaft 30 .
  • the CAC motor 28 also includes a stator 36 having a plurality of stator windings 38 disposed radially outboard of the rotor 32 .
  • the CAC assembly 12 also includes one or more bearings 40 to support rotation of the CAC shaft 30 .
  • a compressor rotor 62 is operably connected to the CAC shaft 30 and rotates about an axis X as driven by the CAC motor 28 .
  • the compressor rotor 62 compresses the air flow 14 to provide a compressed flow 80 in compressor volute 66 of a cabin air compressor housing 68 and directed to a compressor outlet 78 .
  • a cabin air compressor heat housing 34 is coupled to the cabin air compressor housing 68 and includes the compressor inlet 16 configured to receive the air flow 14 .
  • the compressor inlet 16 extends from a body 94 of the cabin air compressor heat housing 34 .
  • the cabin air compressor heat housing 34 supports a diffuser actuator 82 at a diffuser actuator interface 84 .
  • the diffuser actuator 82 further controls the compressed flow 80 .
  • the cabin air compressor heat housing 34 also includes an add-heat valve interface 86 configured to receive an add-heat valve 88 depicted schematically in FIG. 2 .
  • the add-heat valve interface 86 extends transversely from the compressor inlet 16 .
  • the add-heat valve 88 may supply heated air returned from the compressed flow 80 to the compressor inlet 16 to enhance compressor performance of the CAC assembly 12 .
  • the diffuser actuator interface 84 of the cabin air compressor heat housing 34 includes a seal groove 90 that is configured to receive a sealing member 92 , such as an 0 -ring.
  • the diffuser actuator interface 84 and the seal groove 90 are formed in the body 94 of the cabin air compressor heat housing 34 .
  • the sealing member 92 controls leakage flow between the diffuser actuator interface 84 and the diffuser actuator 82 .
  • the compressor inlet 16 , the body 94 of the cabin air compressor heat housing 34 , the add-heat valve interface 85 , and the diffuser actuator interface 84 are formed of a unitary structure, such as a single casting with machined details.
  • a diameter D 1 of the compressor inlet 16 is about 4.555 inches (11.57 cm).
  • a diameter D 2 of the diffuser actuator interface 84 is about 2.347 inches (5.96 cm).
  • a diameter D 3 of the add-heat valve interface 86 is about 3.317 inches (8.43 cm).
  • a width W 1 of the seal groove 90 is about 0.135 inches (0.34 cm).
  • a depth D 4 of the seal groove 90 is about 0.086 inches (0.22 cm).
  • a ratio of the diameter D 1 of the compressor inlet 16 to the diameter D 2 of the diffuser actuator interface 84 is between 1.90 and 1.98.
  • a ratio of the diameter D 1 of the compressor inlet 16 to the diameter D 3 of the add-heat valve interface 86 is between 1.35 and 1.40.
  • a ratio of the diameter D 3 of the add-heat valve interface 86 to the diameter D 2 of the diffuser actuator interface 84 is between 1.40 and 1.42.
  • a ratio of the diameter D 2 of the diffuser actuator interface 84 to the width W 1 of the seal groove 90 is between 16.71 and 18.11.
  • a ratio of the width W 1 of the seal groove 90 to the depth D 4 of the seal groove 90 is between 1.44 and 1.71.
  • a process of installing the cabin air compressor heat housing 34 in the CAC assembly 12 includes coupling the cabin air compressor heat housing 34 to the cabin air compressor housing 68 of the CAC assembly 12 .
  • Sealing member 92 is inserted into the seal groove 90 of the diffuser actuator interface 84 of the cabin air compressor heat housing 34 .
  • the diffuser actuator 82 is coupled to the diffuser actuator interface 84 .
  • the sealing member 92 is compressed in the seal groove 90 between the diffuser actuator interface 84 and the diffuser actuator 82 .
  • the add-heat valve 88 is coupled to the add-heat valve interface 86 of the cabin air compressor heat housing 34 to supply heated air returned from the compressed flow 80 to the compressor inlet 16 .

Abstract

A cabin air compressor heat housing for a cabin air compressor assembly includes a compressor inlet extending from a body of the cabin air compressor heat housing. The cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet. The cabin air compressor heat housing further includes a diffuser actuator interface formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.

Description

    BACKGROUND OF THE INVENTION
  • The subject matter disclosed herein relates to aircraft environmental control. More specifically, the subject disclosure relates to a heat housing of a cabin air compressor for an aircraft environmental control system.
  • Environmental control systems (ECSs) are utilized on various types of aircraft for several purposes, such as in cooling systems for the aircraft. For example, components of an ECS may be utilized to remove heat from various aircraft lubrication and electrical systems and/or used to condition aircraft cabin air. A cabin air conditioner includes one or more cabin air compressors (CACs) which compress air entering the system, from an outside source or from a ram air system. The compressed air is delivered to an environmental control system to bring it to a desired temperature and delivered to the aircraft cabin. After passing through the cabin, the air is typically exhausted to the outside.
    • BRIEF DESCRIPTION OF THE INVENTION
  • According to one aspect, a cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing. The cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet. The cabin air compressor heat housing further includes a diffuser actuator interface formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
  • According to another aspect, a cabin air compressor assembly includes a cabin air compressor heat housing coupled to a cabin air compressor housing. The cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing. The cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet. The cabin air compressor heat housing further includes a diffuser actuator interface formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
  • According to a further aspect, a method of installing a cabin air compressor heat housing in a cabin air compressor assembly includes coupling a cabin air compressor heat housing to a cabin air compressor housing of the cabin air compressor assembly. The cabin air compressor heat housing includes a compressor inlet extending from a body of the cabin air compressor heat housing. The cabin air compressor heat housing also includes an add-heat valve interface extending transversely from the compressor inlet. The cabin air compressor heat housing further includes a diffuser actuator interface having a seal groove formed in the body of the cabin air compressor heat housing. A ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98. The method also includes inserting a sealing member into the seal groove of the diffuser actuator interface. A diffuser actuator is coupled to the diffuser actuator interface. The sealing member is compressed in the seal groove between the diffuser actuator interface and the diffuser actuator.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a partial cross-sectional view of a cabin air compressor assembly;
  • FIG. 2 is a perspective view of a cabin air compressor heat housing;
  • FIG. 3 is a top view of the cabin air compressor heat housing of FIG. 2;
  • FIG. 4 is a partial cross-sectional view of the cabin air compressor heat housing of FIG. 3; and
  • FIG. 5 is a detailed view of a portion of the partial cross-sectional view of the cabin air compressor heat housing of FIG. 4.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • Shown in FIG. 1 is a cross-sectional view of a cabin air compressor (CAC) assembly 12, one or more of which may be used in an environmental control system 100 for an aircraft. The CAC assembly 12 compresses air flow 14 received at a compressor inlet 16. The CAC assembly 12 is driven by a CAC motor 28 operably connected to the CAC assembly 12 via a CAC shaft 30. The CAC motor 28 is an electric motor having a rotor 32 rotatably located at the CAC shaft 30. The CAC motor 28 also includes a stator 36 having a plurality of stator windings 38 disposed radially outboard of the rotor 32. The CAC assembly 12 also includes one or more bearings 40 to support rotation of the CAC shaft 30. In exemplary embodiments, a compressor rotor 62 is operably connected to the CAC shaft 30 and rotates about an axis X as driven by the CAC motor 28. The compressor rotor 62 compresses the air flow 14 to provide a compressed flow 80 in compressor volute 66 of a cabin air compressor housing 68 and directed to a compressor outlet 78.
  • A cabin air compressor heat housing 34 is coupled to the cabin air compressor housing 68 and includes the compressor inlet 16 configured to receive the air flow 14. The compressor inlet 16 extends from a body 94 of the cabin air compressor heat housing 34. The cabin air compressor heat housing 34 supports a diffuser actuator 82 at a diffuser actuator interface 84. The diffuser actuator 82 further controls the compressed flow 80. As depicted in FIG. 2, the cabin air compressor heat housing 34 also includes an add-heat valve interface 86 configured to receive an add-heat valve 88 depicted schematically in FIG. 2. The add-heat valve interface 86 extends transversely from the compressor inlet 16. The add-heat valve 88 may supply heated air returned from the compressed flow 80 to the compressor inlet 16 to enhance compressor performance of the CAC assembly 12.
  • Also as can be seen in FIG. 2, the diffuser actuator interface 84 of the cabin air compressor heat housing 34 includes a seal groove 90 that is configured to receive a sealing member 92, such as an 0-ring. The diffuser actuator interface 84 and the seal groove 90 are formed in the body 94 of the cabin air compressor heat housing 34. The sealing member 92 controls leakage flow between the diffuser actuator interface 84 and the diffuser actuator 82. Collectively, the compressor inlet 16, the body 94 of the cabin air compressor heat housing 34, the add-heat valve interface 85, and the diffuser actuator interface 84 are formed of a unitary structure, such as a single casting with machined details.
  • Referring to FIGS. 2-5, in an embodiment, a diameter D1 of the compressor inlet 16 is about 4.555 inches (11.57 cm). A diameter D2 of the diffuser actuator interface 84 is about 2.347 inches (5.96 cm). A diameter D3 of the add-heat valve interface 86 is about 3.317 inches (8.43 cm). A width W1 of the seal groove 90 is about 0.135 inches (0.34 cm). A depth D4 of the seal groove 90 is about 0.086 inches (0.22 cm).
  • In an embodiment, a ratio of the diameter D1 of the compressor inlet 16 to the diameter D2 of the diffuser actuator interface 84 is between 1.90 and 1.98. A ratio of the diameter D1 of the compressor inlet 16 to the diameter D3 of the add-heat valve interface 86 is between 1.35 and 1.40. A ratio of the diameter D3 of the add-heat valve interface 86 to the diameter D2 of the diffuser actuator interface 84 is between 1.40 and 1.42. A ratio of the diameter D2 of the diffuser actuator interface 84 to the width W1 of the seal groove 90 is between 16.71 and 18.11. A ratio of the width W1 of the seal groove 90 to the depth D4 of the seal groove 90 is between 1.44 and 1.71.
  • A process of installing the cabin air compressor heat housing 34 in the CAC assembly 12 includes coupling the cabin air compressor heat housing 34 to the cabin air compressor housing 68 of the CAC assembly 12. Sealing member 92 is inserted into the seal groove 90 of the diffuser actuator interface 84 of the cabin air compressor heat housing 34. The diffuser actuator 82 is coupled to the diffuser actuator interface 84. The sealing member 92 is compressed in the seal groove 90 between the diffuser actuator interface 84 and the diffuser actuator 82. The add-heat valve 88 is coupled to the add-heat valve interface 86 of the cabin air compressor heat housing 34 to supply heated air returned from the compressed flow 80 to the compressor inlet 16.
  • While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims (20)

1. A cabin air compressor heat housing comprising:
a compressor inlet extending from a body of the cabin air compressor heat housing;
an add-heat valve interface extending transversely from the compressor inlet; and
a diffuser actuator interface formed in the body of the cabin air compressor heat housing, wherein a ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
2. The cabin air compressor heat housing of claim 1, wherein a ratio of a diameter of the add-heat valve interface to the diameter of the diffuser actuator interface is between 1.40 and 1.42.
3. The cabin air compressor heat housing of claim 2, wherein a ratio of the diameter of the compressor inlet to the diameter of the add-heat valve interface is between 1.35 and 1.40.
4. The cabin air compressor heat housing of claim 1, further comprising a seal groove formed in the diffuser actuator interface.
5. The cabin air compressor heat housing of claim 4, wherein a ratio of the diameter of the diffuser actuator interface to a width of the seal groove is between 16.71 and 18.11.
6. The cabin air compressor heat housing of claim 5, wherein a ratio of the width of the seal groove to a depth of the seal groove is between 1.44 and 1.71.
7. The cabin air compressor heat housing of claim 1, wherein the compressor inlet, the body of the cabin air compressor heat housing, the add-heat valve interface, and the diffuser actuator interface are formed of a unitary structure.
8. A cabin air compressor assembly comprising:
a cabin air compressor heat housing coupled to a cabin air compressor housing, the cabin air compressor heat housing comprising:
a compressor inlet extending from a body of the cabin air compressor heat housing;
an add-heat valve interface extending transversely from the compressor inlet; and
a diffuser actuator interface formed in the body of the cabin air compressor heat housing, wherein a ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98.
9. The cabin air compressor assembly of claim 8, wherein a ratio of a diameter of the add-heat valve interface to the diameter of the diffuser actuator interface is between 1.40 and 1.42.
10. The cabin air compressor assembly of claim 9, wherein a ratio of the diameter of the compressor inlet to the diameter of the add-heat valve interface is between 1.35 and 1.40.
11. The cabin air compressor assembly of claim 8, further comprising:
a diffuser actuator;
a sealing member; and
a seal groove formed in the diffuser actuator interface, wherein the diffuser actuator is coupled to the diffuser actuator interface and the sealing member is compressed in the seal groove between the diffuser actuator interface and the diffuser actuator.
12. The cabin air compressor assembly of claim 11, wherein a ratio of the diameter of the diffuser actuator interface to a width of the seal groove is between 16.71 and 18.11.
13. The cabin air compressor assembly of claim 12, wherein a ratio of the width of the seal groove to a depth of the seal groove is between 1.44 and 1.71.
14. The cabin air compressor assembly of claim 8, wherein the compressor inlet, the body of the cabin air compressor heat housing, the add-heat valve interface, and the diffuser actuator interface are formed of a unitary structure.
15. A method of installing a cabin air compressor heat housing in a cabin air compressor assembly comprising:
coupling a cabin air compressor heat housing to a cabin air compressor housing of the cabin air compressor assembly, the cabin air compressor heat housing comprising:
a compressor inlet extending from a body of the cabin air compressor heat housing;
an add-heat valve interface extending transversely from the compressor inlet; and
a diffuser actuator interface having a seal groove formed in the body of the cabin air compressor heat housing, wherein a ratio of a diameter of the compressor inlet to a diameter of the diffuser actuator interface is between 1.90 and 1.98;
inserting a sealing member into the seal groove of the diffuser actuator interface;
coupling a diffuser actuator to the diffuser actuator interface; and
compressing the sealing member in the seal groove between the diffuser actuator interface and the diffuser actuator.
16. The method of claim 15, wherein a ratio of a diameter of the add-heat valve interface to the diameter of the diffuser actuator interface is between 1.40 and 1.42.
17. The method of claim 16, wherein a ratio of the diameter of the compressor inlet to the diameter of the add-heat valve interface is between 1.35 and 1.40.
18. The method of claim 15, wherein a ratio of the diameter of the diffuser actuator interface to a width of the seal groove is between 16.71 and 18.11.
19. The method of claim 18, wherein a ratio of the width of the seal groove to a depth of the seal groove is between 1.44 and 1.71.
20. The method of claim 15, wherein the compressor inlet, the body of the cabin air compressor heat housing, the add-heat valve interface, and the diffuser actuator interface are formed of a unitary structure, and further comprising:
coupling an add-heat valve to the add-heat valve interface.
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US11773746B2 (en) 2021-09-10 2023-10-03 Hamilton Sundstrand Corporation Turbomachinery rotor shroud with variable lattice densities
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