SE124001C1

SE124001C1 -

Info

Publication number: SE124001C1
Authority: SE
Publication date: 1948-01-01

Description

Uppfinnare: W. R. Hawthorne. Inventor: W. R. Hawthorne.

Prioritet begeird frrin den 29 mars 1944 (Storbritannienl. Priority sought before March 29, 1944 (Great Britain.

Foreliggande uppfinning hanfor sig till fOrbranningsturbinaggregat av den typ, som vanligtvis benamnes »dubbel kompoundtyp och som uppvisar tvh mekaniskt oberoende rotorer, som kunna rotera med olika varytal och av vilka -var och en bestar av en kompressor och en med denna till en enhet sunmanbyggd turbin samt namnda rotorer sâ inbordes forbindande luft- och gaskanaler, att luft passerar i faljd genom lag- och hogtryckskompressorerna och darefter genom en farbranningsapparat, i vilken bransle insprutas och farbrannes kontinuerligt, varefter de gasformiga forbranningsprodukterna expanderas genom hog- och lhgtrycksturbinerna pa sadant satt, att dessa bringas ati driva sina resp. kompressorer. The present invention relates to combustion turbine assemblies of the type commonly referred to as the "double compound type" which have two mechanically independent rotors which can rotate at different speeds and each of which consists of a compressor and a turbine built therein. and said rotors so that connecting air and gas ducts are embedded so that air passes in succession through the law and high pressure compressors and then through a combustion apparatus, in which fuel is injected and combusted continuously, after which the gaseous combustion products are expanded through the high and low pressure turbines. these are brought to drive their resp. compressors.

Foreliggande uppfinning banfOr sig vidare till vissa modifikationer av ett farbranningsturbinaggregat ax angivet slag, genom vilka deli as nyttoeffekt och i -vissa fall Oxen verkningsgrad kan avsevart stegras genom an-vandande av hterupphettning, vilken fiatadkommes gcnom att extrabransle insprutas och forbrannes i de gasformiga forbranningsprodukterna ph ett eller flera stallen mellan narbelagna turbiner eller turbinsteg, eller enlist vilka effekt uttages ayen Iran en sarskild effektturbin, vilken drives av de expanderande avgaserna. Den mest effektiva och elastiska driften av en anlaggning av angivet slag erhalles, om hogtrycksturbinen far driva hogtryckskompressorn och lagtryckskompressorn far drivas av lagtrycksturbinen. The present invention further relates to certain modifications of a combustion turbine assembly of the type indicated, by which the efficiency of the deli and in some cases the efficiency of the oxen can be considerably increased by the use of reheating, which is achieved by injecting extra fuel and combustion products into the gaseous products. one or more stalls between adjacent turbines or turbine stages, or enlist which power is extracted ayen Iran a special power turbine, which is driven by the expanding exhaust gases. The most efficient and elastic operation of a plant of the specified type is obtained, if the high-pressure turbine is allowed to drive the high-pressure compressor and the low-pressure compressor is allowed to be driven by the low-pressure turbine.

Ett andainal med foreliggande uppfinning är att anpassa ett krattaggregat av angivet slag for att anvandas som motor for en dragande flygplanspropeller, d. v. s. ett bladeller skovelforsett framdrivningsorgan, placerat vid anlaggningens i flygriktningen hetraktat framre ande. I dylikt fall är det onskvart att driva propellern med hjalp av lagtrycksturbinen far att erna sa Mgt utvaxlingsf5rhallande som madligt far en emellan dessa komponenter eventuellt anordnad ut-vaxlingsanordning. Da det galler en dragande propeller, uppsta emellertid, sarskilt om en axialturbin kommer till anvandning, svarigheter med att uppna detta iinskvarda resultat och samtidigt iistadkomma den grad av sammantrangdhet i konstruktionen, som fordras av en kraftmaskin for drivning av flygplan, samt tillfredsstalla de ytterligare fordringarna, att lagtrycksturbinen skall driva lagtryckskompressorn och avgiva avgaserna i riktning nedstranns, utan att darigenom f5rorsakas en icke onskvard komplicering av gaskanalsystemet. Samtliga dessa svarigheter overvinnas genmn foreliggande uppfinning, enligt Aiken Rireslas ett fOrbrOnningsturbinaggregat ay dubbel hornpoundtyp av angivet slag, konstruerat som motor for en dragande flygplanspropeller, och -vilket generellt kannetecknas av en kombination av en rotoranordning, besthende av en lagtryckskompressorrotor och en lagtrycksturbinrotor, samt en andra rotoranordning, besthende av en hogtryckskompressorrotor och en hogtrycksturbinrotor, vilka rotoranordningar Oro roterbara oberoende av varandra samt anordnade koaxiellt, sO att lagtrycksturbinen, lagtryckskompressorn, hogtryckshompressorn och hogtrycksturbinen Oro belagna i nu namnd ordningsfoljd bakifran och framat i aggregatet raknat (med avseende pa flygriktningen), saint en propellerdrivaxel, som Or drivande forbunden med la.gtrycksrotorn och stracker sig koaxiellt genom hogtrycksrotorn, sO att det erhalles ett av lagtrycksrotorn drivet och far en dragande propeller lampligt effektuttag vid aggregatets franare ande. An object of the present invention is to adapt a rake assembly of the type indicated to be used as an engine for a towing aircraft propeller, i.e. a blade or vane-propelled propulsion means, located at the forward end of the plant in the direction of flight. In such a case, it is inconvenient to operate the propeller with the aid of the low-pressure turbine, so that the gear ratio is as variable as that of a gearing device possibly arranged between these components. As a traction propeller is required, however, especially if an axial turbine is used, it is difficult to achieve this difficult result while at the same time achieving the degree of design constraint required by an aircraft power machine, and satisfying the additional requirements. , that the low-pressure turbine should drive the low-pressure compressor and emit the exhaust gases in the downstream direction, without thereby causing an undesirable complication of the gas duct system. All these responsibilities are overcome by the present invention, according to Aiken Rireslas, a dual horn pound type combustion turbine assembly of the type indicated, designed as an engine for a traction aircraft propeller, and which may generally be characterized by a combination of a rotor device, a low pressure rotor and a compression rotor. second rotor device, consisting of a high-pressure compressor rotor and a high-pressure turbine rotor, which rotor devices are rotatable independently of each other and arranged coaxially, so that the low-pressure turbine, the high-pressure compressor, the high-pressure compressor and the high pressure turbine saint a propeller drive shaft, which Or is drivingly connected to the low pressure rotor and extends coaxially through the high pressure rotor, so that one is obtained driven by the low pressure rotor and has a traction propeller suitable power outlet at the franar of the unit e ande.

I allmanhet torde en nedvaxlingsanordning yam erforderlig i propellertransmissionen I andamal att astadkomma ett godtagbart propellervarvtal, beroende pa propellerns karakteristika, och i enlighet med ett ytterligare uppfinningskannetecken Or en dylik nedvaxlingsanordning (reduktionsvaxel) eller ett i denna ingaende steg placerat mellan hog- och 2— — lagtrycksrotorerna. Genom att sâ placera reduktionsvaxeln eller nagon del av densamma blir det mojligt att sakerstalla att propellerns drivaxel roterar med sadant varvtal, att de kritiska virvelhastigheter, son( eljest skulle uppsth kring denna axel, undvikas. In general, a downshift device should be required in the propeller transmission in order to provide an acceptable propeller speed, depending on the characteristics of the propeller, and in accordance with a further inventive feature, or such a downshift device (reduction gear) or a step the legal pressure rotors. By placing the reduction shaft or some part thereof, it becomes possible to ensure that the propeller shaft of the propeller rotates at such a speed that the critical vortex velocities, which would otherwise arise around this shaft, are avoided.

I enlighet med uppfinningen drives alItsa en dragande propeller, som fir anordnad fram- for dubbelkompoundmotorn, antingen direkt eller Over en uMixling, av en effektaxel, som stracker sig axiellt genom hogtrycksrotorn och med sin bakre ande Or drivande kopplad till lagtrycksrotorn Over en reduktionsvaxel, som Or belagen mellan de hada kompressorerna. In accordance with the invention, a traction propeller, which is arranged in front of the twin-compound engine, either directly or via a mixer, is driven by a power shaft which extends axially through the high-pressure rotor and with its rear end or driven coupled to the low-pressure rotor via a reduction shaft. Or coated between the hada compressors.

Ehuru denna anordning har den nackdelen att hogtrycksrotorn mhste vara central!: ge- nomborrad for genomforing av den dragande propellerns krafttransmissionsaxel, gor den det mojligt aft draga en lamplig drivanordning for propellern frail lagtrycksrotorn utan- att det blir nodvandigt att gasernas stromningsriktning ornkastas efter det de passerat genom lhgtrycksturbinen, vilken omkastning av stromningsriktningen skulle yam forknippad med ett sá stort tryckfall, att motorns verkningsgrad skulle avsevart forsamras. An- ordningen gOr det ocksh molligt att Ora axelledningen mellan lagtrycksturbinen och lagtryckskompressorn kort, sa att risken. Nor att gaserna skola hinna antaga hoga virvelhastigheter avsevart reduceras. Although this device has the disadvantage that the high-pressure rotor must be central !: pierced for the passage of the traction propeller of the traction propeller, it makes it possible to pull a suitable drive device for the propeller from the low-pressure rotor without it being necessary to expose the gases in the direction of flow. passed through the low pressure turbine, which reversal of the flow direction would be associated with such a large pressure drop that the efficiency of the engine would be considerably reduced. The device also makes it possible to shorten the shaft line between the low-pressure turbine and the low-pressure compressor, so that the risk. Nor that the gases should have time to assume high vortex velocities are significantly reduced.

Uppfinningen skall i det foljande beskrivas mera detaljerat med hjalp av bifogade rit- ning, som visar en halv langdsektion och en halv sidoprojektion av en dubbelkompoundmotor, avsedd att anvandas som en flygmotor, som arbetar med dragande propeller. The invention will be described in more detail below with the aid of the accompanying drawing, which shows a half longitudinal section and a half side projection of a twin-compound engine, intended for use as an aircraft engine operating with traction propellers.

I den ph ritningen visade utfOringsformen innefattar den dubbla kompoundmotorn en lagtrycks axialturbin, en lagtrycks axialkom- pressor, en hogtrycks axialkompressor, en ringformig farbranningskammare och en hog- trycks axialturbin, samtliga anordnade koaxiellt och i namnda ordningsfOljd bakifrAn och frinnat inuti en motorgondol 10. In the embodiment shown in the drawing, the double compound engine comprises a low-pressure axial turbine, a low-pressure axial compressor, a high-pressure axial compressor, an annular combustion chamber and a high-pressure axial turbine, all arranged coaxially and in said order in the opposite direction from the rear.

Lfigtrycksturbinen och lagtryekskompressorn ha en gemensam rotor av sarnmansatt form innefattande ett skovelforsett turbin- hjul 11 samt en skovelforsedd kompressortrumma 12, vilka hada Oro monterade ph en langsghende axel 13, som Or roterbart lagrad i lager 14. Turbinhjulet 11 arbetar i ett skovelforsett turbinstatorhus 15, som stoder sig pA det bakre lagret 14 medelst en cirkular tvfirvagg 16, och kompressortrumman 12 arbetar i ett skovelftirsett statorhus 17, vars bakre Oxide Or fast till en inloppsring 18, vilken har en bakatriktad konisk fOrlfingning 19, vilken stodes av det namnda bakre lagret 14. The low pressure turbine and the low pressure compressor have a common rotor of assembled shape comprising a vaned turbine wheel 11 and a vaned compressor drum 12, which had Oro mounted on a longitudinal shaft 13 rotatably mounted in bearing 14. The turbine wheel 11 operates in a vaned turbine housing 15. which rests on the rear bearing 14 by means of a circular two-pronged wall 16, and the compressor drum 12 operates in a vane-stator stator housing 17, the rear Oxide Or of which is fixed to an inlet ring 18, which has a rearwardly directed conical finger 19, which is supported by the said rear bearing 14 .

PA liknande satt ha hogtrycksturbinen och hogtryckskompressorn en gemensam rotor av sammansatt form, vilken innefattar en skovelforsedd kompressorrotortrumma 20, som medelst en framatriktad konisk forlangning 21 är forbunden riled ett skovelforsett turbinhjul 22, varvid derma sammansatta rotor pa lager 24 Or lagrad for fri rotation kring en axel 23, som genomgar densamma i langdriktningen, varvid det bakre lagret 24 stoder rotortrummans 20 bakre ande medelst en tvarvfigg 25 och varvid det friimre lagret 24 Or inneslutet i spetsen av den koniska forlfingningen 21. Rotortrumman 20 arbetar i ett skovelforsett statorhus 26 och turbinhjulet 22 arbetar i ett skovelfOrsett statorhus 27: dessa statorhus 26, 27 firo forbundna med varandra medelst en kort ring 28 och en cylindrisk trumma 29, som omsluter rotortrummans 20 koniska forlangning 21, varvid statorhuset 27 Or stott pa. axeln 23 medelst ett lager 30, belaget omedelbart framfor turbinhjulet 22, saint medelst ett andra lager 31, belaget i spetsen av en frainfitriktad konisk forlangning 32, vilken an fast till del namnda statorhuset 27. Similarly, the high pressure turbine and the high pressure compressor have a common rotor of composite shape, which comprises a vane-mounted compressor rotor drum 20, which by means of a forwardly conical extension 21 is connected to a vane-mounted turbine wheel 22, the composite rotor being mounted thereon 24 shaft 23, which undergoes the same in the longitudinal direction, the rear bearing 24 supporting the rear end of the rotor drum 20 by means of a turning fig 25 and the outer bearing 24 being enclosed in the tip of the conical extension 21. The rotor drum 20 operates in a vaned stator housing 26 and the turbine wheel 22 operates in a vane-mounted stator housing 27: these stator housings 26, 27 are connected to each other by means of a short ring 28 and a cylindrical drum 29, which encloses the conical extension 21 of the rotor drum 20, the stator housing 27 being supported on. shaft 23 by means of a bearing 30, coated immediately in front of the turbine wheel 22, saint by means of a second bearing 31, coated at the tip of a non-aligned conical extension 32, which is fixed in part to said stator housing 27.

En ringformig forbranningskammare 33, i vilken briinsle insprutas och forbriinnes kontinuerligt av brannarmunstycken 34 (ay vilka endast ett ar visat pa ritningen), forbinder kornpressorhusets 26 utloppsring 28 med inloppet till hogtrycksturbinhuset 27 och hagtrycksturbinens avlopp Or medelst riirledningar 35 forbundet med inloppet till lagtrycksturbinhuset 15, varvid namnda rorledningar 35 forlopa genom motorgondolen 10 och Oro forsedda med ett alerupphettningsmunstycke 36 Mr insprutning och forbranning av brfinsle i gasstrommen mellan turbi nerna. An annular combustion chamber 33, into which fuel is continuously injected and combusted by burner nozzles 34 (of which only one is shown in the drawing), connects the outlet ring 28 of the grain presser housing 26 to the inlet to the high pressure turbine housing 27 and the high pressure turbine inlet to the pressure vessel. said pipelines 35 passing through the engine gondola 10 and Oro provided with an aluminum heating nozzle 36 for injecting and burning fuel in the gas stream between the turbines.

:Wilful de bada mekaniskt oberoende rotorernas kompressordelar Or anordnad en reduktionsvaxel 37, som drives av lagtrycksrotorns axel 13 och som driver den axel 23, som forloper frainat axiellt genom hogtrycksrotorn, varvid namnda reduktionsvfixel Or monterad inuti en ringformig kanaldel 38, silken fiirbinder de hada kompressorernas ringformiga genomstromningskanaler rued varandra och vid sin bakre uncle stodes av (let framre lagret 14 och en med ringen i ett stycke utford hjultallrik 39 och vid sin framre ande av en tvarvagg 40 och ett lager 41 pa axeln 23. Denna axel 23 driver de motroterande delarna 42, 43 av en framfor motorgondolen 10 anordnad dragande dubbelpropeller. Arranged by the compressor parts of the two mechanically independent rotors Or arranged a reduction shaft 37, which is driven by the shaft 13 of the low pressure rotor and which drives the shaft 23 which extends axially through the high pressure rotor, said reduction shaft Or being mounted inside an annular channel part 38. annular flow channels rued each other and at its rear uncle stood off (the front bearing 14 and one with the ring in one piece challenge wheel plate 39 and at its front end of a turret 40 and a bearing 41 on the shaft 23. This shaft 23 drives the counter-rotating parts 42, 43 of a towing double propeller arranged in front of the motor gondola 10.

Under driften insuges luft i motorn fran det gransskikt, som passerar onakring motorgondolen 10, genom radiella och framatriktade inloppskanaler 44 (av vilka endast en Or visad ph ritningen), som leda till inloppsringen 18, varefter luften passerar genom lag- och hogtryckskompressorerna i serie och fortsatter till forbranningskamrarna 33. De gasformiga farbranningsprodukterna Iran forbranningskanuarna 33 expanderas partiellt genom hogtrycksturbinen i och fOr driv- - -3 ning av hogtrycks-turbin-kompressorrotorn (20, 21, 22, 25) och aterupphettas i rorledningarna 35, innan de expanderas genom Mgtrycksturbinen i och for drivning av lagtrycksturbin-kompressorrotorn (11, 12, 13) samt, -Over reduktionsvaxeln 37 och axeln 23, den dragande dubbelpropellern 42, 43. During operation, air is drawn into the engine from the boundary layer passing on the engine nacelle 10 through radial and forward inlet channels 44 (of which only one is shown in the drawing), leading to the inlet ring 18, after which the air passes through the series and high pressure compressors in series and proceeding to the combustion chambers 33. The gaseous combustion products Iran the combustion vessels 33 are partially expanded through the high pressure turbine in and for driving the high pressure turbine compressor rotor (20, 21, 22, 25) and reheated in the pipelines 35 before being expanded by the turbine in and for driving the low pressure turbine compressor rotor (11, 12, 13) and, -Over the reduction shaft 37 and the shaft 23, the trailing twin propeller 42, 43.

Eventuellt aterstaende energi I avloppsgaserna fran lagtryeksturbinen kan pa i och for -sig kant satt utnyttjas till att alstra reaktionsdrivkraf t. Any remaining energy in the waste gases from the low-pressure turbine can be used in a different way to generate reaction driving force.

Claims

Patenta.nsprak:

A dual-compound combustion turbine unit, designed as a motor for a traction air propeller, characterized by a combination of a rotor device, consisting of a low-pressure compressor rotor (12) and a low-pressure turbine rotor (11), and a second rotor device, consisting of a high-pressure compressor rotor a high-pressure turbine rotor (22), which rotor devices are rotatable independently of each other and arranged coaxially, so that the low-pressure turbine (11), the low-pressure compressor (12) the high-pressure compressor (20) and the high-pressure turbine (22) are coated in the aforementioned sequence with respect to the direction of flight), and a plug or drive shaft (23), which is drivingly connected to the low pressure rotor (11, 12) and extends coaxially through the high pressure rotor (20, 21, 22), so that an air pressure rotor driven and f The pulling propeller (42, 43) is suitable for the power outlet at the front of the unit.

2. A combustion turbine unit according to claim 1, characterized in that a reduction shaft (37), which engages in the transmission from the low-pressure rotor (11, 12) to the power take-off of the propeller (42, 43), is located between the low-pressure rotor (11, 12) and the high-pressure rotor (20 , 21, 22) and drive connected to the former and to the drive shaft (23) of the propeller (42, 43).

Combustion turbine unit according to claim 2, characterized in that the turbines (11, 15; 22, 27) are of axial type.

4. Combustion turbine assemblies according to any one of the preceding claims, characterized in that the high pressure rotor (20, 21, 22) is mounted for rotation on the axially extending power transmission shaft (23) while forming axially spaced ball or roller bearings ( 24). Stockholm 1949, Ic.um41. Boktr. P. A. Norstmlt & SiMer 450080