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Publication numberUS2367223 A
Publication typeGrant
Publication dateJan 16, 1945
Filing dateApr 7, 1942
Priority dateApr 7, 1942
Publication numberUS 2367223 A, US 2367223A, US-A-2367223, US2367223 A, US2367223A
InventorsLarrecq Anthony J
Original AssigneeGen Electric
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Combined centrifugal compressor and cooler
US 2367223 A
Abstract  available in
Images(1)
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Claims  available in
Description  (OCR text may contain errors)

Jan. 16; 1945. A. J. LARRECQ COMBINED CENTRIFUGAL COMPRESSOR AND CO0LER Filed April '7, 1942 v Ihx'xenqm: Anthony J Larrecq, by w adw His Attorn e Q Patented Jan. 16, 1945 COMBINED CENTRIFUGAL comasssoa AND COOLER AnthonyJ. Larrecq, Indianapolis, Ind., assignor to General Electric Company, a corporation of New York application April 7, 1942, Serial No. 438,000

Claims.

The present-invention relates to centrifugal compressors and especially to centrifugal compressors such as are used on aircraft as superchargers, although its use is not limited thereto necessarily.

In connection with such centrifugal compressors, there is required usually a cooler or heat exchanger, for cooling the air discharged from the compressor, and the object of my invention is to provide an improvedconstruction and arrangement of centrifugal compressor and cooler wherein the cooler is built into and forms aunitary part of the compressor.

For a consideration of what I believe to be novel and my invention, attention is directed to the following specification and the claim appended thereto.

In the drawing, Fig. 1 is a side elevation, partly in section, of a supercharger embodying my invention,-a supercharger of the gas turbine driven type being illustrated in the present instance; Fig, 2 is a detailed perspective view of a part of the cooler or heat exchanger; and Fig. 3 shows the structure mounted on an aircraft.

Referring to the drawing, I indicates a 'shaft mounted in a bearing 2 and having on one end a turbine wheel 3 and on the other end a comby a wall I1 and at the other edge by a wall l8 which forms a part of discharge scroll l3. The parts may be held in assembled relation by suitable tie bolts l9 or by other suitable means. At

20 is an admission conduit for supplying air to both the cooler or heat exchanger and to the compressor. Conduit 20 may take air from any suitable source. dinarily receives air from a ram facing into the slip streamwhereby air is forced through the conduit to the cooler and the eye of the impeller, building up a positive pressure in front of the eye of the impeller; This is shown in Fig. 3

-wherein 2| indicates in outline an aircraft and pressor impeller '4, the impeller being held in Y position by a nut 5 on the end of shaft l. Adjacent to the turbine wheel is an annular nozzle box 6 having a ring of nozzles I which serve to direct gases 'to the buckets of the .turbine wheel. The nozzle box inlet 8 may be connected with the exhaust manifold of an aircraft engine whereby it receives exhaust gases from the engine. This is 'a known type of gas driven turblue and requires no further explanation. ,Its

specific-construction forms no part of the present invention. 7

Impeller 4 is located in a compressor casing 9x and surrounding the impeller is a ring of circumferentially spaced curved diffuser vanes In which define diffuser passages through which air discharged from the periphery of the impeller flows and which function to convert the velocity of the air into pressure in a well understood .manner. From the diffuser passages air flows to the radial outer portion l2 of the compressor casing and thence axially to an annular discharge chamher or scroll l3. from which it flows outwardly through a discharge conduit l4 which may connect-with a point of consumption for the air,

for example, the intake manifold on anaircrai't engine. The eye of the impeller is indicated at Ii; It stands in line with the inlet II to the compressor casing.

Located between the radially'outer portion I2 of. the compressor casing and the discharge scroll 'II is an annular air cooler or'heat exchanger II supported at one edge from the compressor inlet apart the cells to define axially extending pas- 22 indicates a ram connected to conduit and facing into the slip stream.

Cooler or heat exchanger l6 may be of any suitable construction, the essential thing being that it has passages for thefiow of the air from the. compressor (the air to be cooled) axially to the diffuser I3 and interspersed passages for the flow of coolingair radially outward. In both Figures 1 and 2, the arrows A indicate the direction of now of the air to be cooled and arrows B indicate the direction of fiow of the cooling air. Referring particularly to Fig. 2, the cooler is shown in the present instance as comprising a plurality of cells each comprising two spaced plates 23 and 24 connected along opposed edges as is indicated at 25 to define radially extending passages 26 for the cooling air. A plurality of cells are" spaced circumferentially relatively to each other and are structurally united to define an annular cooler. The cells are spaced by means of spacer strips 21 and 28 which space sages 29 for flow of the air to be cooled. The radially outer spacers 28 are somewhat wider in a circumferential direction than are the spacers 21 to take care ofthedifference in diameters between the radially outer and radially inner sides of the cooler.

If desired, adjustable louvers 30 may be arranged in conduit 20 to control the flow of air to the compressor and to the cooler.

In operation, air enters through conduit 20 and divides, a part of it entering the eye of the impeller and theremainder flowing radially outward through the cooling air passages 26. The air which enters the eye of the impeller is discharged radially from the impeller to the diffuser from which it travels axially through the passages 29. of the cooler to discharge scroll I! and thence out through conduit l4 to the point of consumption.

The air which effects the cooling flows radially outward through passages 28 and is discharged to atmosphere. In flowing along the walls 23 and 24 the cooling air absorbs heatfrom the air flowing through passages 29'.

In the case of an aircraft, it or- Owing to the ram effect, i. e., the forced flow of air through conduit 20 by reason of the ram 22 facing into the slip stream, a positive pressure is built up inside the cooler and in front of the 'eye of the impeller sufficient to effect flow of cooling air through the cooler.

By my invention, I provide an improved construction which is relatively light in weight (a thing of great importance in the case of aircraft), compact, and eificient in operation. By utilizing a single air inlet for both the compressor and the cooler, there is required only a single conduit and ram for conveying air to both. This, I regard as an important feature of my invention.

From another viewpoint, my invention comprises a centrifugal type compressor which has a casing with a central inlet for medium to be compressed and an outlet for compressed meoperating medium such as air to the compressor and to the cooling passages formed between the channel members.

In accordance with the provisions of the patent statutes, I have described the principle of operation of my invention, together with the apparatus which I now consider to represent the best embodiment thereof, but I desire to have it understood that the apparatus shown is only illustrative and that the invention may be carried out by other means.

What I claim asnew and desire to secure by Letters Patent of the United States, is:

1. A combined centrifugal compressor and cooler comprising a compressor casing having an admission opening, a discharge scroll, a cooler located between said casing and scroll and forming a common conduit for conveying fluid to both the compressor and the cooler.

2. In combination, a compressor having an inlet and an annular discharge area concentrically surrounding the inlet, an annular discharge chamber spaced axially from said discharge area, and an annular row of spaced cooling tubes connected betweensaid discharge area and said discharge chamber.

3. A compressor having a casing with a central inlet and a structure surrounding the inlet and attached to the casing comprising a cooler and a discharge chamber, and a common inlet for the cooler and central inlet formed by a wall of the discharge chamber.

4. A compressor having a casing with a central inlet and walls defining a. discharge area, an annular cooler attached to said walls through which medium to be'cooled fiows axially from said discharge area and cooling medium flows radially, and walls forming a discharge chamber attached to said cooler and forming a conduit for conducting coolingmedium to the cooler and medium to be compressed to the compressor.

5. In combination, a centrifugal impeller, a casing for the impeller having an inlet and walls forming a discharge area surrounding the impeller, an annular cooler surrounding said inlet and attached to said walls, said cooler having axially extending passages for flow of medium from said discharge area and radially extending passages for flow of cooling medium, and walls attached to said cooler to form a discharge chamber and a conduit connected to said walls for conducting medium to both the cooler and the compressor.

4 6. In combinations. centrifugal impeller, a casing for the impeller having an inlet and walls forming a discharge area surrounding the impeller, an annular cooler surrounding said inlet and attached to said walls, said cooler having axially extending passages for flow of medium from said discharge area and radially extending passages for flow of cooling medium, walls attached to said cooler to form a discharge chamber, and a common supply inlet for said impeller and cooler formed at least partly by said last mentioned walls. 1

7. For use on an aircraft, a supercharger comprising a centrifugal impeller, a casing member having walls forming a discharge area surrounding the impeller, an annular cooling member attached to said casing member and having passages for the flow of cooling air and passages for the flow of air to be cooled, and a common inlet formed by one of said members for supplying air to said impeller and cooler.

8. In combination, a centrifugal compressor having a casing forming an inlet, and an annular discharge area on the same side as and concentrically spaced from the inlet, a discharge scroll axially spaced from the annular discharge area, a plurality of circumferentially spaced channel members for conducting compressed medium from the discharge area to the scroll, said channel members forming substantially radial passages between them with inlet openings for directly receiving a part of the medium flowing towards the inlet of the casing.

9. In combination, a compressor having a casing with a central inlet for conducting medium to be compressed to an impeller chamber formed by the casing, said casing having walls forming an annular row of discharge openings concentrically spaced from and located on the same side of the casing as said inlet, and means for conducting medium to be compressed to the compressor and for cooling compressed medium discharged therefrom, said means comprising an annular row of circumferentially spaced axial channel members having inlets connected to said discharge openings and a discharge scroll connected to the outlets of said channel members, said scroll having an inner wall forming a conduit for medium to be conducted to the inlet of the compressor and to cooling passages formed between said channel members.

10. In combination, a centrifugal compressor having a central inlet for medium to be compressed and a cooler for cooling compressed medium discharged from the compressor, said cooler having two axially spaced annular headers of which one is in part formed by the compressor casing and a plurality of axial circumferentially spaced channel members connected between the headers and forming cooling passages between them, the inlets to said passages surrounding concentrically the inlet to the compressor casing. and one of said headers forming a. channel for conducting operating medium to the inlet of the compressor and to said cooling passages.

ANTHONY J'. LARRECQ.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2581964 *Mar 16, 1945Jan 8, 1952Garrett CorpCooling system for air supplied to compartments of aircraft
US2637984 *Jul 26, 1950May 12, 1953Gen ElectricTurbine
US2646027 *Feb 28, 1951Jul 21, 1953Curtiss Wright CorpAftercooler construction
US2792200 *Mar 15, 1952May 14, 1957Modine Mfg CoToroidal type heat exchanger
US3038318 *Jun 2, 1958Jun 12, 1962Sulzer AgExpansion turbine and turbocompressor connected therewith in a cold producing plant
US3417577 *Jun 3, 1966Dec 24, 1968Cloyd D WaldronRoom air purifier
US3828573 *Jun 20, 1973Aug 13, 1974M EskeliHeating and cooling wheel
US6216774 *Oct 17, 1997Apr 17, 2001Honda Giken Kogyo Kabushiki KaishaHeat exchanger
US6526751 *Dec 17, 2001Mar 4, 2003Caterpillar IncIntegrated turbocharger ejector intercooler with partial isothermal compression
US6557345 *Dec 17, 2001May 6, 2003Caterpillar IncIntegrated turbocharger fan intercooler with partial isothermal compression
US6715713 *May 21, 2003Apr 6, 2004Airbus FranceExchanger for aircraft air conditioning circuit and integrated propulsion assembly for such an exchanger
Classifications
U.S. Classification62/467, 165/166, 159/28.1, 244/53.00R, 60/599, 62/401
International ClassificationF04D29/58, F02B33/00
Cooperative ClassificationF04D29/5826, F02B33/00, F02M2700/33
European ClassificationF02B33/00, F04D29/58C2