US3638719A - Heat exchanger - Google Patents

Heat exchanger Download PDF

Info

Publication number
US3638719A
US3638719A US346197A US3638719DA US3638719A US 3638719 A US3638719 A US 3638719A US 346197 A US346197 A US 346197A US 3638719D A US3638719D A US 3638719DA US 3638719 A US3638719 A US 3638719A
Authority
US
United States
Prior art keywords
pipes
bundle
header means
heat exchange
heat exchanger
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.)
Expired - Lifetime
Application number
US346197A
Inventor
Rodney Mcgann
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.)
Texaco Inc
Original Assignee
Texaco Inc
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 Texaco Inc filed Critical Texaco Inc
Application granted granted Critical
Publication of US3638719A publication Critical patent/US3638719A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28FDETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F21/00Constructions of heat-exchange apparatus characterised by the selection of particular materials
    • F28F21/08Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
    • F28F21/081Heat exchange elements made from metals or metal alloys
    • F28F21/084Heat exchange elements made from metals or metal alloys from aluminium or aluminium alloys
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12Cooling of plants
    • F02C7/14Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22Fuel supply systems
    • F02C7/224Heating fuel before feeding to the burner
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28DHEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D7/00Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/005Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for only one medium being tubes having bent portions or being assembled from bent tubes or being tubes having a toroidal configuration
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28DHEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D7/00Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
    • F28D7/0058Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for only one medium being tubes having different orientations to each other or crossing the conduit for the other heat exchange medium
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28FDETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F19/00Preventing the formation of deposits or corrosion, e.g. by using filters or scrapers
    • F28F19/002Preventing the formation of deposits or corrosion, e.g. by using filters or scrapers by using inserts or attachments
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28FDETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F21/00Constructions of heat-exchange apparatus characterised by the selection of particular materials
    • F28F21/08Constructions of heat-exchange apparatus characterised by the selection of particular materials of metal
    • F28F21/081Heat exchange elements made from metals or metal alloys
    • F28F21/082Heat exchange elements made from metals or metal alloys from steel or ferrous alloys
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28HEAT EXCHANGE IN GENERAL
    • F28FDETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2250/00Arrangements for modifying the flow of the heat exchange media, e.g. flow guiding means; Particular flow patterns
    • F28F2250/02Streamline-shaped elements
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S165/00Heat exchange
    • Y10S165/355Heat exchange having separate flow passage for two distinct fluids
    • Y10S165/40Shell enclosed conduit assembly

Definitions

  • RODNEY Mc GANN HEATEXCHANGER This invention relates to improvements in heat exchangers and, in particular, to an improved heat exchanger for use in air breathing reaction engines of the type wherein a portion of the energy of the ram air is transferred to the fuel by heat exchange between the ram air and the fuel.
  • the heat exchanger will cool the ingested difiused air so that the engine downstream of the heat exchange will not be subjected to temperatures exceeding, for example, that corresponding to about Mach 3 (about 650 F.) during Mach 8 flight conditions and the airstream having passed the heat exchanger is more easily compressed.
  • a heat exchanger including a bundle of substantially parallel pipes, the ends of which present a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, input header means supplying fluid to one end of the pipes in the bundle and outlet header means withdrawing fluid from the other end of the pipes in the bundle.
  • the invention is also embodied in such a heat exchanger wherein the length and the relative displacement of the pipes in the bundle is such that the total transverse area of the pipes in any transverse plane through the bundle is substantially less than the total projected transverse area of the pipes in the bundle.
  • FIG. 1 is a generally diagrammatic view in partial transverse cross section of an air-breathing reaction propulsion engine employing a ram air heat exchanger constructed in accordance with the teachings of the present invention
  • FIG. 2 is a front end view of the structures illustrated in FIG.
  • FIG. 3 is a schematic section through the heat exchanger illustrated in FIG. 2 illustrating the parallel arrangement of the bundle of heat exchange pipes of the heat exchanger;
  • FIG. 4 is an enlarged fragmentary partial sectional view of one heat exchange pipe of the bundle of pipes of the heat exchanger shown in FIGS. 1 and 2 including a portion of its forward and rearward header means.
  • FIG. 1 generally designates an air-breathing reaction engine of the type wherein a portion of the energy of the ram air entering the forward end of the engine is transferred to the fuel by heat exchange between the ram air and the fuel as disclosed and claimed in, for example, application Ser. No. 324,957, R. L. Wolf and Rodney McGann, Reaction Propulsion Engine and Method of Operation," filed Nov. 20, 1963 and assigned to applicant's assignee.
  • the reaction engine 10 includes a shell 12 having a forward end 14 and a rearward end 16.
  • the forward end 14 of the shell or casing 12 connects to the inlet duct for ram air, the path of the ram air being indicated by the directional arrows A.
  • the indirect heat exchange means 18 of the invention In the forward end 14 of the ram air passage is the indirect heat exchange means 18 of the invention.
  • the heat exchange means 18 has the outer surface of the heat exchange elements thereof in contact with the ram air entering the engine while the internal surface of the indirect heat exchange means provides a path for the flow of fuel from the fuel tank 20.
  • Fuel from the fuel tank 20 is directed by pump 24 through a conduit 22, thence through conduit 26 to a main rear header 28.
  • Fuel, after passing through the heat exchanger 18, is directed therefrom via a forward main header means 30, thence through conduit 32 to a fuel flow regulating mechanism generally designated 34.
  • a portion of the fuel is directed to the turbine 36 and a portion of the fuel may be directed to a regenerative heat exchanger 38 positioned in the combustion chamber 40 for the reaction engine and/or a portion may be directly expanded into the combustion chamber via conduit 42.
  • the turbine 36 drives a compressor 44 which compressor compresses air entering the ram air inlet 14 after the air has been cooled in its passage through the heat exchange means 18. The products of combustion of the fuel and the compressed air and any excess fuel or excess air issue fromthe nozzled outlet 16 of the reaction engine.
  • the rear header means 28 is connected to the forward header means 30 by a bundle 50 of heat exchange pipes 52.
  • the rearward ends 54 of each of the pipes may be constructed of aluminum, the forward portion 56 of the pipes 52 may be constructed of, for example, columbium, while the intermediate section 58 may be constructed of steel.
  • the single pass counterflow arrangement of the heat exchange tubes permits the use of less exotic materials in the rear or cooler part of the heat exchanger thereby not only reducing the weight of the assembly but also the cost of materials of construction.
  • the bundle of heat exchange pipes 50 is connected to the rearward header means 28 through a plurality of secondary header pipes 60.
  • Each of the header pipes 60 has one end in fluid communication with the primary header 28 and each of the secondary header pipes 60 spirals generally inwardly and forwardly as more clearly illustrated in FIGS. 1 and 2 of the drawings.
  • the most inner and forward end of each of the secondary header pipes 60 is closed and each of the secondary headers 60 controls the flow of fluid to a plurality of the heat exchange pipes 52 of the bundle of pipes 50.
  • a similar arrangement of secondary generally spirally arranged forward headers 62 connect the forward ends of the heat exchange pipes 52 of the bundle of pipes 50 to the forward primary header 30. It will be noted that in the illustrated form of the invention, the spiral array of secondary headers 60 and 62 are so formed that the bundle 50 of substantially parallel heat exchange pipes 52 present a convex configuration at one end of the bundle and a concave configuration at the other or rearward end of the bundle.
  • the concave and convex surfaces need not be segments of spheres but may comprise other conoidal configurations without departing from the scope of the invention.
  • the radius of curvature as illustrated in FIG. 3, is greater than the length L of each of the heat exchange pipes 52 by a distance S whereby the total transverse area of the pipes 52 in any transverse plane through the bundle 50 is substantially less than the total projected transverse area of the pipes 52 of the bundle 50. Therefore, the maximum tube blockage to the passage of air thereabout is only a portion of the tube blockage which would result if all of the tubes started in the same transverse plane.
  • the forward header means may be provided with a ceramic or other heat resistant shield 64 aerodynamically shaped to minimize turbulence and to present a minimum area to the flow of air and to minimize damage to the heat exchange by the ingestion of harmful objects such as birds.
  • the forward primary header 30 is connected to conduit 32 through a slip joint or flexible connector 66; therefore, all axial expansion is taken up in the single joint.
  • the forward primary header 30 may be rigidly attached to the vehicle and the rearward primary header 28 may be connected to the conduit 26 through a suitable expansion joint whereby axial expansion would only be in the rearward direction toward the compressor 44 or each header may be connected to its respective pipe by a suitable heat expansion joint.
  • the heat exchanger of the present invention may be readily tailored for a particular reaction engine or vehicle mission by merely increasing or decreasing the axial length of the heat exchanger assembly without changing the fundamental design parameters of the device.
  • a heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, and outlet header means withdrawing fluid from the other end of the pipes in said bundle.
  • each of the pipes of said parallel bundle of pipes is the same length.
  • each of the pipes of the bundle of pipes is constructed of a plurality of segments difiering in composition with the most heat resistant composition having connection to the outlet header means.
  • a heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, outlet header means withdrawing fluid from the other end of the pipes in said bundle, said inlet header means and said outlet header means including a plurality of generally spiral segments connecting opposite ends of a plurality of said pipes of the bundle of pipes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

A heat exchanger comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, and outlet header means withdrawing fluid from the other end of the pipes in said bundle.

Description

t! o a "l M, Elite tatee att [151 3,638,719
MeGann 1 Feb. 1, 1972 [54] HEAT EXCHANGER 683,267 11/1939 Germany ..158/ 822,759 10/1959 Great Britain ..l65/164 [72] Inventor: Rodney McGann, Northridge, Calif.
[73] Assignee: Texaco, Inc, New York, NY. Emmi'lersamuel Engle Attorney-Stowe" and Stowell [22] Filed: Feb. 20, 1964 21 Appl 34 197 EXEMPLARY CLAIM A heat exchanger comprising a bundle of substantially parallel 52 us. C1 ..l65/164, /267 p p the ends of Said P p Presenting a convex configuration [51] Int. Cl ..F28d 7/04 at one end of e bu d e and a conca e configuration at the [58] Field of Search ..165/ 164, 165, 166, 167, 175, other end of the bundle, h l ng h and h r l iv displace- 165/176, 158, 180, 133, 172; 60/267 ment of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said [56] References Cited bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying UNITED STATES PATENTS fluid to one end of the pipes in said bundle, and outlet header 2,745,797 5/1956 Long ..l/180 means Withdrawing fluid fmm the other end of the Pipes in 2,817,499 12/1957 Harding et al .....165/180 Said bundle- 2,856,161 10/1958 Flynn ..165/ X 5 Claims, 4 Drawing Figures PATENTED FEB 1m: 3.638.719
INVENTOR.
RODNEY Mc GANN HEATEXCHANGER This invention relates to improvements in heat exchangers and, in particular, to an improved heat exchanger for use in air breathing reaction engines of the type wherein a portion of the energy of the ram air is transferred to the fuel by heat exchange between the ram air and the fuel.
It has been found that by locating a heat exchanger in the air inlet of air breathing reaction engines, the heat exchanger will cool the ingested difiused air so that the engine downstream of the heat exchange will not be subjected to temperatures exceeding, for example, that corresponding to about Mach 3 (about 650 F.) during Mach 8 flight conditions and the airstream having passed the heat exchanger is more easily compressed.
It is, therefore, a principal object of the present invention to provide a single pass, counterflow, high-temperature air cooling heat exchanger having generally low weight and low-frontal area with a minimum of pressure loss.
These and other objects and advantages of the present invention are provided in a heat exchanger including a bundle of substantially parallel pipes, the ends of which present a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, input header means supplying fluid to one end of the pipes in the bundle and outlet header means withdrawing fluid from the other end of the pipes in the bundle. The invention is also embodied in such a heat exchanger wherein the length and the relative displacement of the pipes in the bundle is such that the total transverse area of the pipes in any transverse plane through the bundle is substantially less than the total projected transverse area of the pipes in the bundle.
The invention will be more fully described in reference to the illustrative embodiments thereof shown in the accompanying drawings wherein:
FIG. 1 is a generally diagrammatic view in partial transverse cross section of an air-breathing reaction propulsion engine employing a ram air heat exchanger constructed in accordance with the teachings of the present invention;
FIG. 2 is a front end view of the structures illustrated in FIG.
FIG. 3 is a schematic section through the heat exchanger illustrated in FIG. 2 illustrating the parallel arrangement of the bundle of heat exchange pipes of the heat exchanger; and
FIG. 4 is an enlarged fragmentary partial sectional view of one heat exchange pipe of the bundle of pipes of the heat exchanger shown in FIGS. 1 and 2 including a portion of its forward and rearward header means.
Referring to the drawings and, in particular, to FIG. 1, generally designates an air-breathing reaction engine of the type wherein a portion of the energy of the ram air entering the forward end of the engine is transferred to the fuel by heat exchange between the ram air and the fuel as disclosed and claimed in, for example, application Ser. No. 324,957, R. L. Wolf and Rodney McGann, Reaction Propulsion Engine and Method of Operation," filed Nov. 20, 1963 and assigned to applicant's assignee.
In general, the reaction engine 10 includes a shell 12 having a forward end 14 and a rearward end 16. The forward end 14 of the shell or casing 12 connects to the inlet duct for ram air, the path of the ram air being indicated by the directional arrows A. In the forward end 14 of the ram air passage is the indirect heat exchange means 18 of the invention. The heat exchange means 18 has the outer surface of the heat exchange elements thereof in contact with the ram air entering the engine while the internal surface of the indirect heat exchange means provides a path for the flow of fuel from the fuel tank 20.
Fuel from the fuel tank 20 is directed by pump 24 through a conduit 22, thence through conduit 26 to a main rear header 28. Fuel, after passing through the heat exchanger 18, is directed therefrom via a forward main header means 30, thence through conduit 32 to a fuel flow regulating mechanism generally designated 34. From the fuel flow regulating mechanism 34 a portion of the fuel is directed to the turbine 36 and a portion of the fuel may be directed to a regenerative heat exchanger 38 positioned in the combustion chamber 40 for the reaction engine and/or a portion may be directly expanded into the combustion chamber via conduit 42. The turbine 36 drives a compressor 44 which compressor compresses air entering the ram air inlet 14 after the air has been cooled in its passage through the heat exchange means 18. The products of combustion of the fuel and the compressed air and any excess fuel or excess air issue fromthe nozzled outlet 16 of the reaction engine.
Now, referring to FIGS. 1 through 4, in the heat exchange means 18 in the illustrated form of the invention, the rear header means 28 is connected to the forward header means 30 by a bundle 50 of heat exchange pipes 52. As illustrated in FIG. 4, the rearward ends 54 of each of the pipes may be constructed of aluminum, the forward portion 56 of the pipes 52 may be constructed of, for example, columbium, while the intermediate section 58 may be constructed of steel. Thus, the single pass counterflow arrangement of the heat exchange tubes permits the use of less exotic materials in the rear or cooler part of the heat exchanger thereby not only reducing the weight of the assembly but also the cost of materials of construction.
The bundle of heat exchange pipes 50 is connected to the rearward header means 28 through a plurality of secondary header pipes 60. Each of the header pipes 60 has one end in fluid communication with the primary header 28 and each of the secondary header pipes 60 spirals generally inwardly and forwardly as more clearly illustrated in FIGS. 1 and 2 of the drawings. The most inner and forward end of each of the secondary header pipes 60 is closed and each of the secondary headers 60 controls the flow of fluid to a plurality of the heat exchange pipes 52 of the bundle of pipes 50. lnterconnecting a plurality of the heat exchange tubes 52 to the generally spiral secondary header pipes 60 has the particular advantage that thermal expansion of the headers will bring about rotation of the segments rather than primarily radial growth, thereby keeping to a minimum the necessity for expansion joints and the like in the system.
A similar arrangement of secondary generally spirally arranged forward headers 62 connect the forward ends of the heat exchange pipes 52 of the bundle of pipes 50 to the forward primary header 30. It will be noted that in the illustrated form of the invention, the spiral array of secondary headers 60 and 62 are so formed that the bundle 50 of substantially parallel heat exchange pipes 52 present a convex configuration at one end of the bundle and a concave configuration at the other or rearward end of the bundle.
It will be appreciated, however, that the concave and convex surfaces need not be segments of spheres but may comprise other conoidal configurations without departing from the scope of the invention. Further, in the illustrated form of the present invention, the radius of curvature, as illustrated in FIG. 3, is greater than the length L of each of the heat exchange pipes 52 by a distance S whereby the total transverse area of the pipes 52 in any transverse plane through the bundle 50 is substantially less than the total projected transverse area of the pipes 52 of the bundle 50. Therefore, the maximum tube blockage to the passage of air thereabout is only a portion of the tube blockage which would result if all of the tubes started in the same transverse plane. This arrangement, however, increases the overall length of the heat exchanger but normally in aircraft installations, the frontal area is substantially more critical than the length of the vehicle. An ideal compromise between the length of the heat exchanger and the total area of tube blockage results when the maximum tube blockage is from about 50 percent to about percent of the blockage which would result from having all of the tubes start in the same plane. A maximum tube blockage of about 70 percent of the blockage resulting from having all of the tubes start in the same plane is preferred.
it will also be noted that the defined results are achievable even though the convex forward end and the concave rearward end of the heat exchange do not define similar surfaces.
lt will be further apparent from the schematic cross section illustrated in FIG. 3 that preferably for equal heat transfer area per square foot of air flow area in, for example, a cylindrical duct that heat exchange tubes 52 should be distributed proportional to the area contained in each segment of the tube bundle. Therefore, as the forward and rearward secondary segments 60 and 62 spiral forwardly and inwardly, the spacing between the pipes on each segment would increase to main tain the preferred uniform or equal transfer area per square foot of flow area in the duct.
Further, as illustrated more clearly in FIG. 4 of the drawings, the forward header means may be provided with a ceramic or other heat resistant shield 64 aerodynamically shaped to minimize turbulence and to present a minimum area to the flow of air and to minimize damage to the heat exchange by the ingestion of harmful objects such as birds.
As illustrated in FIG. 1 of the drawings, the forward primary header 30 is connected to conduit 32 through a slip joint or flexible connector 66; therefore, all axial expansion is taken up in the single joint. it will be appreciated that the forward primary header 30 may be rigidly attached to the vehicle and the rearward primary header 28 may be connected to the conduit 26 through a suitable expansion joint whereby axial expansion would only be in the rearward direction toward the compressor 44 or each header may be connected to its respective pipe by a suitable heat expansion joint. Further, the heat exchanger of the present invention may be readily tailored for a particular reaction engine or vehicle mission by merely increasing or decreasing the axial length of the heat exchanger assembly without changing the fundamental design parameters of the device.
From the foregoing description considered with the illustrated embodiments of the invention, it will be seen that the novel heat exchange fully accomplishes all of the aims and objects hereinbefore set forth.
lclaim:
1. A heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, and outlet header means withdrawing fluid from the other end of the pipes in said bundle.
2. The invention defined in claim 1 wherein each of the pipes of said parallel bundle of pipes is the same length.
3. The invention defined in claim 1 wherein each of the pipes of the bundle of pipes is constructed of a plurality of segments difiering in composition with the most heat resistant composition having connection to the outlet header means.
4. A heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, outlet header means withdrawing fluid from the other end of the pipes in said bundle, said inlet header means and said outlet header means including a plurality of generally spiral segments connecting opposite ends of a plurality of said pipes of the bundle of pipes.
5. The invention defined in claim 4 wherein said inlet header means is provided with a heat resistant, streamlines coating.
* =i e a

Claims (5)

1. A heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, and outlet header means withdrawing fluid from the other end of the pipes in said bundle.
2. The invention defined in claim 1 wherein each of the pipes of said parallel bundle of pipes is the same length.
3. The invention defined in claim 1 wherein each of the pipes of the bundle of pipes is constructed of a plurality of segments differing in composition with the most heat resistant composition having connection to the outlet header means.
4. A heat exchange comprising a bundle of substantially parallel pipes, the ends of said pipes presenting a convex configuration at one end of the bundle and a concave configuration at the other end of the bundle, the length and the relative displacement of the pipes in said bundle being such that the total transverse area of the pipes in any transverse plane through said bundle is substantially less than the total projected transverse area of the pipes of the bundle, input header means supplying fluid to one end of the pipes in said bundle, outlet header means withdrawing fluid from the other end of the pipes in said bundle, said inlet header means and said outlet header means including a plurality of generally spiral segments connecting opposite ends of a plurality of said pipes of the bundle of pipes.
5. The invention defined in claim 4 wherein said inlet header means is provided with a heat resistant, streamlines coating.
US346197A 1964-02-20 1964-02-20 Heat exchanger Expired - Lifetime US3638719A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US34619764A 1964-02-20 1964-02-20

Publications (1)

Publication Number Publication Date
US3638719A true US3638719A (en) 1972-02-01

Family

ID=23358366

Family Applications (1)

Application Number Title Priority Date Filing Date
US346197A Expired - Lifetime US3638719A (en) 1964-02-20 1964-02-20 Heat exchanger

Country Status (1)

Country Link
US (1) US3638719A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2215538A1 (en) * 1973-01-26 1974-08-23 Texaco Development Corp
FR2218485A1 (en) * 1973-02-16 1974-09-13 Texaco Development Corp
FR2219315A1 (en) * 1973-02-22 1974-09-20 Texaco Development Corp
DE3827828A1 (en) * 1987-08-15 1991-12-05 Rolls Royce Plc HEAT EXCHANGER
US20120255715A1 (en) * 2011-04-07 2012-10-11 Hamilton Sundstrand Corporation Liquid-to-air heat exchanger
US20150101308A1 (en) * 2013-10-11 2015-04-16 Reaction Engines Ltd Engine
US9302776B2 (en) 2012-08-15 2016-04-05 Hamilton Sundstrand Corporation Ram outlet header
WO2020239899A3 (en) * 2019-05-30 2021-03-11 Reaction Engines Limited Engine
EP3889535A1 (en) * 2020-02-07 2021-10-06 Raytheon Technologies Corporation Duct mounted heat exchanger
WO2022051849A1 (en) * 2020-09-08 2022-03-17 Pradeep Dass Turboramjet engine
EP4033192A3 (en) * 2013-10-11 2022-08-10 Reaction Engines Limited Heat exchangers
US12031502B2 (en) * 2019-05-30 2024-07-09 Reaction Engines Limited Gas turbine engine having a heat exchanger arrangement having at least one heat exchanger module overlapping another heat exchanger module

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE683267C (en) * 1936-12-22 1939-11-02 Arthur Schoke Heating element for evaporator or cooker
FR1100242A (en) * 1953-05-08 1955-09-19 Tech Studien Ag heat exchanger with multiple exchanger tubes, in particular for thermal power plants using gaseous working fluid
US2745797A (en) * 1953-01-19 1956-05-15 Gen Motors Corp Electroplating pipe joint
US2817499A (en) * 1955-03-03 1957-12-24 Combustion Eng Steam generator
US2856161A (en) * 1955-01-07 1958-10-14 Elwin E Flynn Heat transfer apparatus
GB822759A (en) * 1957-02-18 1959-10-28 Serck Radiators Ltd Heat exchangers

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE683267C (en) * 1936-12-22 1939-11-02 Arthur Schoke Heating element for evaporator or cooker
US2745797A (en) * 1953-01-19 1956-05-15 Gen Motors Corp Electroplating pipe joint
FR1100242A (en) * 1953-05-08 1955-09-19 Tech Studien Ag heat exchanger with multiple exchanger tubes, in particular for thermal power plants using gaseous working fluid
US2856161A (en) * 1955-01-07 1958-10-14 Elwin E Flynn Heat transfer apparatus
US2817499A (en) * 1955-03-03 1957-12-24 Combustion Eng Steam generator
GB822759A (en) * 1957-02-18 1959-10-28 Serck Radiators Ltd Heat exchangers

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2215538A1 (en) * 1973-01-26 1974-08-23 Texaco Development Corp
FR2218485A1 (en) * 1973-02-16 1974-09-13 Texaco Development Corp
FR2219315A1 (en) * 1973-02-22 1974-09-20 Texaco Development Corp
DE3827828A1 (en) * 1987-08-15 1991-12-05 Rolls Royce Plc HEAT EXCHANGER
DE3827828C2 (en) * 1987-08-15 2000-11-30 Rolls Royce Plc Heat exchanger
US9151539B2 (en) * 2011-04-07 2015-10-06 Hamilton Sundstrand Corporation Heat exchanger having a core angled between two headers
US20120255715A1 (en) * 2011-04-07 2012-10-11 Hamilton Sundstrand Corporation Liquid-to-air heat exchanger
US9302776B2 (en) 2012-08-15 2016-04-05 Hamilton Sundstrand Corporation Ram outlet header
US20150101308A1 (en) * 2013-10-11 2015-04-16 Reaction Engines Ltd Engine
US10012177B2 (en) * 2013-10-11 2018-07-03 Reaction Engines Ltd Engine comprising a rocket combustion chamber and a heat exchanger
EP4033192A3 (en) * 2013-10-11 2022-08-10 Reaction Engines Limited Heat exchangers
US11661888B2 (en) 2013-10-11 2023-05-30 Reaction Engines Ltd. Heat exchangers
WO2020239899A3 (en) * 2019-05-30 2021-03-11 Reaction Engines Limited Engine
US20220220924A1 (en) * 2019-05-30 2022-07-14 ReactionEngines Limited Engine
US12031502B2 (en) * 2019-05-30 2024-07-09 Reaction Engines Limited Gas turbine engine having a heat exchanger arrangement having at least one heat exchanger module overlapping another heat exchanger module
EP3889535A1 (en) * 2020-02-07 2021-10-06 Raytheon Technologies Corporation Duct mounted heat exchanger
US11650018B2 (en) 2020-02-07 2023-05-16 Raytheon Technologies Corporation Duct mounted heat exchanger
WO2022051849A1 (en) * 2020-09-08 2022-03-17 Pradeep Dass Turboramjet engine

Similar Documents

Publication Publication Date Title
US11421598B2 (en) Staggered heat exchanger array with side curtains
CN106959034B (en) Heat exchanger for embedded engine application
EP0173774B1 (en) Gas turbine engine
US3638719A (en) Heat exchanger
US2465099A (en) Propulsion means comprising an internal-combustion engine and a propulsive jet
US2162956A (en) Aircraft power plant
CN109989831B (en) Heat exchanger with integrated diffuser
US11982232B2 (en) Aircraft heat exchangers
US2487842A (en) Aircraft power plant apparatus
US10358976B2 (en) Heat recuperation system for the family of shaft powered aircraft gas turbine engines
CN106958485B (en) Heat exchanger for embedded engine application: curve ruler
US3267673A (en) Recuperator for gas turbine powerplants
US5484122A (en) Turbine exhaust gas anti-ice system
US3249306A (en) Automatically adjustable rocket nozzle
US3377803A (en) Jet engine cooling system
US2783613A (en) Cooling system employing fuel for cooling the blades of gas turbine engines
US4203283A (en) Combustion chamber, especially annular reverse-flow combustion chamber for gas turbine engines
US3775977A (en) Liquid air engine
GB2217828A (en) Heat exchangers
US2525804A (en) Aircraft rotary boiler turbine air condenser power plant
US2801518A (en) Gas turbine
US3477505A (en) Heat exchanger
US6422020B1 (en) Cast heat exchanger system for gas turbine
US2631430A (en) Gas turbine power plant having coaxially arranged combustors and regenerator
US11274602B2 (en) Air cooler for gas turbine engine