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Publication numberUS2855754 A
Publication typeGrant
Publication dateOct 14, 1958
Filing dateDec 31, 1953
Priority dateDec 31, 1953
Publication numberUS 2855754 A, US 2855754A, US-A-2855754, US2855754 A, US2855754A
InventorsGiannottl Hugo V
Original AssigneeGiannottl Hugo V
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Gas turbine with combustion chamber of the toroidal flow type and integral regenerator
US 2855754 A
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Description  (OCR text may contain errors)

Oct. 14, 1958 .v H. v. GIANNOTTI 2,855,754 GAS TURBINE WITH COMBUSTION CHAMBER OF THE TOROIDAL I FLOW TYPE AND INTEGRAL REGENERATOR Filed Dec. 31, 1953 V 3 Sheets-Sheet 1 w T T 3 w *Y N N & M \Q T T Z 1 2 9 IN V EN TOR.

Oct. 14, 1958 H. v. GIANNOTTI 7 2,355,754


BY a r/ A6,": f fizzy/amt Oct. 14, 1958 H. v. GIANNOTTI 2,855,754


Application December. 31,1953,,Serial-No.'401,6ll3: 4 Claims; (Cl; 60 -3936) This invention relates. to. improvements iill. gas turbines and has for its. principaliobjectsxthe; compactness.- of. structureand the increase in. .performanceof suchturbinest In the conventional gasttu-rbineunitair orother oxidizing' gas is. compressedand fuel injectedin-a: combustion chamber forburning. Thecombustion. gasthus formed issupplied to a turbine-whichzin turn rotates: an. impeller to etfect an. initial compression of the air; Power. may be derived from the unitteither by direct mechanicalzconnection with. the turbine shaft or: from the reaction of the gas discharged from .the unit asin the case of. the jet pro:- pulsion engine. The. instantinvention is applicable to either field since it deals the tu-rbineportionirom which. power. can be derived: eitherv through the: torque furnished-by the turbine wheelffrom the'exhaust gasesof combustion or'frorn the: reaction. of. the; gas; discharged from. the turbine;

It is a feature: of this; invention: to; combine: into: one combustion chamber thez'salutaryfeatures of; therannular type and the cannulartype combustionchambersr whereby the annular. discharge from thecompressor'wilhmaintain a constant pressure gradientialong its: outlet: and wherein alongzflame path. is maintainediso=as1to efiectgoofl per.- formance within the combustionzchamber;

It is. a. further feature of this invention to: effect: a: reductionin. overall diameter, length and. weight so as tod'ecrease the. cost of mauufacture and tovin'crease the operating performanceofthe gas turbine.

It is a further. object of this. invention to provide regeneration to the combustion. chamber; inlet. air: so asto increase the overall efficiency of the gasturbine.

Further objects and features of the. invention will: be apparentfrom the following. description. taken in connectionwith. the accompanying. drawings, in which:

Fig. l is a longitudinal. section; of onef form. of gas.

turbine embodied in the principles of the invention, and

Fig. 2 isa sectionalview taken substantially'on the line 22 of Figure 1, and

Fig.3 is a sectional view taken substantially on the-line 3'-3 of Figure 2.

Fig. 4 is a sectional view of a multiple unit. combustion chamber.

In order to facilitate an understanding of the invention, reference is made to the embodiment selected for the purpose of illustration, and specific language is usedwto" describe the same. It will, nevertheless, be appreciated that no limitation of the scope of the invention is thereby intended, and that such further modifications and alterations of the structure and function of the parts herein described are contemplated as would be efi'ected by those skilled in the art without the exercise of invention.

Referring now to Figure 1, it Will be observed that the illustrated unit consists on the left hand side of an electric alternator schematically drawn as an example of a load on the gas turbine. The power unit itself appears on the right hand side of Figure 1, and has its shaft coupled to the shaft of the generator. The power unit ice 21 illustrated in Figure 1 shown in, longitudinalcross section, isr a:. centrifugal: compressor-centripetal turbine type of gas turbi-ne but it istunderstood thatthe invention is not limitedxto this specificity-pe. of gas turbine.

Starting'atthe right hand. edge-of the. electricv alternator load; the-turbine shaft12 is..connected. by gearing or any suitable means to the-generator shaft. The-turbine shaft istjournalled in bearingsdof the antifriction type which arermounted in'the' shaft housing 6; Thezturbine shaft'2 is; integrally? connected with the. rotor assembly 8 (as viewedv in Fig; 1) but it may be directly connected by any'suitable means such as a spline. connectionv tothe rotor assembly 8,. whose lefthand face; (as view'ed in Fig: 1.) forms the-impeller 10- for the:- radial flowscompressor unit, and. whose right: hand. face forms the wheel, for the: turbine 12.

Proceeding axially from the rotor assembly 8, the ex+ haust diffuser 1'4: is bounded by the: cylindrical wall- 16 which carries: outward to a finned wall 18 to the exhaust outlet-of the turbine;

The outer-casing 20 of the gas turbine has: an air inlet opening 22 wherein the'inlet air enters andjis-compressed by the centrifugal, compressor 10 and is discharged into the annular outer passageway 26; which isboundedby the outer shell 20 and theinner wall 30 of the outer pas sageway'26. The outer passageway26 extends axially the entire: length of the turbine where it mergestangentially into the toroidal combustion chamber 32. The inner wall 300i theouter passageway 26 may extend, as shown,.part way' around a circle centered on the annular axis of the: toroidal combustionchamber 32-, and contains apertures 3'4 inxthat portion of its length adjacent the-combustion chamber 32. The inner wall 30is cl'osed oif'for a portion of its circumference (as viewedin Fig. 2') ad'- jacent the: discharge outlet 36 so as to insure that all of the entering primary air will bein the combustion chamber 32' at acircumferential' distancebefore the discharge outlet 36 to insure proper and complete burning and mixing.

The combustion chamber 32 is generally toroidal in shape divided by a baffle plate 38 (as viewed in Fig; 3') which. is transverse to the combustion chamber 32 and adjacent the discharge outlet 36: The bafiie plate 38 divides the combustion chamber 32 so that the entering primary air must circulate around the circumference of the chamber in one direction toward the discharge outlet 36.. Further, the burned gases cannot recirculate around the combustion chamber but must discharge through the discharge outlet 36 into the plenum chamber 40.

It will be evident that in this" construction air for come busti'on comes to the toroidal combustion chamber 32 in an axially flowing annular sheet through the an nular passageway 26 around chamber 40, and then because of' thetangential. relation. to: a circle about the annular: axis of the toroidal. chamber 32,. this inflowing sheet of air enters the toroid. in such; a way as to be curled inwardly (so to speak) around that annular axis by the curvature of the outer wall of the; combustion. chamber. Within the toroid, air is fed radially inward from this sheet toward the annular axis of the combustion chamber and, except near the discharge outlet 36 where the inner wall 30 is closed off, a part of the sheet of air sweeps around the combustion chamber wall in a circular direction (with reference to the annular axis of the combustion chamber), while air is also being carried in a direction along the annular axis of the combustion chamber to the outlet. There is at least one localized outlet providing an axial flow discharge to the chamber 40. Thus the air does not pass from combustion chamber inlet to outlet by a course directly across the circular section of the toroid, but passes around a substantial arcuate part of the length of the combustion chamber toroid, affording a substantial length of combustion path, with air being fed radially toward the annular axis of the toroid for combustion along that path.

The plenum chamber 40 is bounded by the inner wall 30 of the outer passageway 26 and by the wall 16 of the exhaust chamber 14. The burning gases entering the plenum chamber 40 circulate around the plenum chamber which provides further mixing of the gases before discharging into the turbine nozzles 44.

The hot gases exit from the plenum chamber through the turbine nozzles 44 which are mounted by any suitable means, as for example by welding, between plenum chamber wall 16 and the inner wall 30 of the outer passageway 26 so that the hot gases are directed against the blades of the turbine wheel 12, whence they are discharged into the exhaust chamber 14 and pass the finned wall 18. The hot gases impinging on the turbine wheel force that wheel to rotate and thus provide the output power for the gas turbine.

The discharge outlet of the unit being the center of the toroidally shaped combustion chamber 32 provides regeneration for the entering primary air, by reason of the heat exchange effected through the common wall 18 of the hot exhaust gases in the exhaust chamber 14 and the cooler primary air of the outer passageway 26, thereby raising the temperature of such primary air, thus requiring less fuel to being such primary air to its operating temperature and thereby increasing the overall efiiciency.

The fuel necessary for combustion is injected into the combustion chamber 32 by the fuel injector 46 (as viewed in Fig. 2) which may be mounted by any suitable means on the outer surface of the combustion chamber 32 near the partition 38 and on its side away from the outlet 36. The mixture of fuel and air is ignited by the igniter 48 which too is mounted on the outer surface of the combustion chamber 32.

It should be understood that the combustion chamber 1 32 may be made in two or more sections (as appears in Fig. 4) instead of one section as illustrated in Figs. l-3 so that the-toroidal combustion chamber will contain two or more complete sections, each with a separate bafile plate, separate discharge outlet, separate fuel injector and separate igniter. Each section will act as a complete combustion chamber and will discharge the burning gases into the same plenum chamber. Such a multiple arrangement will increase the overall efliciency of the gas turbine.

The toroidal combustion chamber 32 bounded by the outer casing 20 and the inner wall 30 of the outer passageway 26 for a portion of its circumference is such as -to insure that the entering primary air will follow a toroidal path thereby materially decreasing the actual .peripheral length of the chamber required to-obtain proper mixing and burning characteristics. The air admission ference of such portion of the. inner wall 30, thereby insuring further and proper mixing of such primary air.

I claim: 1. A combustion chamber for use with a gas turbine comprising an outer casing having an arcuate inner liner which divides the. chamber into an outer passageway and an inner passageway wherein combustion takes place, a duct for introducing inlet air into the outer passageway about the outer periphery of the casing, so that air flows about the edge of the liner into the inner passageway, a portion of the wall of the casing being cut away to form a discharge outlet, and a baffie extending transversely of the inner passageway adjacent the outlet, the portion of the edge of the liner adjacent the outlet connecting with the casing to separate the inner and outer passageway so that air cannot pass directly from the inlet duct into the outlet without passing through the inner passageway.

2. A combustion chamber according to claim 1 wherein the linear is provided with aplurality of apertures which extend between the inner and outer passageways thereby supplying some portion of the secondary air for the combustion taking place in the inner passageway.

3. In a gas turbine having a compressor and a turbine on a common axis of rotation, a fixed toroidal combustion chamber around said axis, means defiining an annular passage for air extending from the compressor outlet to the outer part of the toroidal combustion chamber in tangential relation thereto, relative to a circle about the annular axis of the toroidal chamber, whereby over a substantial arcuate length of said toroidal chamber air sweeps around the outer wall of said chamber on a circle about its annular axis and also along said annular axis, with flow radially inward toward said annular axis, together with at least one localized outlet in the wall of said combustion chamber providing discharge for combustion gases, a partition across said chamber adjacent said outlet to block flow along said annular axis, and a fuel inlet and ignition means adjacent said partition on its side away from said outlet, whereby combustion occurs over an extended path from fuel inlet to chamber outlet with addition of air to the combustion mixture along said path.

4. A combination as in claim 3 in which the compressor acts centrifugally and the turbine acts centripetally, the toroidal combustion chamber is at the discharge side of said turbine and there is an inner, annular, axially extending partition spaced from said air passage means and connecting with the inner wall of said toroidal combustion chamber to define an annular plenum chamber on its outer side and a generally cylindrical exhaust chamber on its inner side, the said plenum chamber being in communication with the turbine inlet at one side and with the combustion chamber outlet at the other side, and said cylindrical chamber receiving the turbine exhaust at one side and discharging at its other side through the central opening of the combustion chamber toroid, to effect heat exchange between the turbine discharge gas and air sweeping 'the wall of the combustion chamber.

References Cited in the file of this patent UNITED STATES PATENTS 2,085,761 Lysholm July 6, 1937 2,611,241 Schulz Sept. 23, 1952 2,658,338 Leduc Nov. 10, 1953 2,748,568 Budworth June 5, 1956 FOREIGN PATENTS 717,179 Germany Feb. 7, 1942

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2085761 *Feb 14, 1934Jul 6, 1937Milo AbAircraft power plant
US2611241 *Mar 19, 1946Sep 23, 1952Packard Motor Car CoPower plant comprising a toroidal combustion chamber and an axial flow gas turbine with blade cooling passages therein forming a centrifugal air compressor
US2658338 *Feb 21, 1948Nov 10, 1953Leduc ReneGas turbine housing
US2748568 *Feb 8, 1952Jun 5, 1956Dutton Budworth DavidFuel injection arrangement in vortex air stream in an annular combustion chamber surrounding a gas turbine
DE717179C *Apr 19, 1940Feb 7, 1942Maschf Augsburg Nuernberg AgSchwungkraftanlasser fuer Brennkraftmaschinen
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2946192 *May 16, 1958Jul 26, 1960Standard Motor Co LtdGas turbine power plant
US3010281 *Dec 24, 1957Nov 28, 1961Cervenka Adolph JToroidal combustion chamber
US3163003 *Feb 27, 1961Dec 29, 1964Garrett CorpGas turbine compressor
US4151709 *Nov 26, 1976May 1, 1979Avco CorporationGas turbine engines with toroidal combustors
US5174108 *Sep 23, 1991Dec 29, 1992Sundstrand CorporationTurbine engine combustor without air film cooling
US5526640 *May 16, 1994Jun 18, 1996Technical Directions, Inc.Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall
US7127897 *Feb 2, 2004Oct 31, 2006Alstom Technology Ltd.Combustion chamber
US7237385Jun 30, 2006Jul 3, 2007Alstom Technology Ltd.Method of using a combustion chamber for a gas turbine
US7318317Mar 1, 2007Jan 15, 2008Alstom Technology Ltd.Combustion chamber for a gas turbine
DE1233660B *Jan 28, 1964Feb 2, 1967Rolls RoyceRingfoermige Verbrennungsanlage fuer Gasturbinenstrahltriebwerke
U.S. Classification60/804, 60/755
International ClassificationF02C7/08
Cooperative ClassificationF02C7/08
European ClassificationF02C7/08