00:Home

10:Aircrafts

20:Carriers

30:Bases

40:Maps

50:R.O.E.

60:Crews

70:More

80:Story

90:Missions

See also :

Piston Engines

Turboprop Engines

Jet Engines

Rocket Engines

2017-11-20

ENGINES

DB600 Series

DB601A

DB601N

DB603

DB605A

DB605AM


  Article  

Reproduced from : http://kurfurst.org/index.html
     
     
 

DB 601A-1

 
     
     

Documents

1.

Datasheet

2.

This paper is a later DB 601A-1 datasheet via Messerschmitt AG, Augsburg dated 25 July 1941. Of special interests is that the paper notes a further increase in permissable RPM: by July 1941 the latest, up to 2800 rpm is possible above rated altitude, as opposed to the 2600 rpm mentioned in the previous paper. Furthermore the increased RPM was by now obtainable with automatic RPM control (i.e. the automatic propeller pitch control or "Verstellautomatik") as opposed to the previously used manual override/pitch control.

3.

-

4.

Document - Source: Betriebs- und Wartungsvorschrift zum Mercedes-Benz Flugmotor DB 601 A u. B, Ausgabe C, Oktober 1940.   Daimler-Benz Aktiengesellschaft, Stuttgart-Untertürkheim.

5.

Power curve for DB 601A-1 with early type supercharger with 4 km rated altitude

6.

Power curve for DB 601A-1 with new type supercharger with 4,5 km rated altitude - Source: Betriebs- und Wartungsvorschrift zum Mercedes-Benz Flugmotor DB 601 A u. B, Ausgabe C, Oktober 1940.  Daimler-Benz Aktiengesellschaft, Stuttgart-Untertürkheim

7.

Power curve for DB 601A-1 with new type supercharger with 4,5 km rated altitude, showing rammed power of 0 to 1200 kg/sq.m and specific fuel consumption  -  Source: Daimler-Benz Aktiengesellschaft, curve no. 9-601-2213, 12 August 1940.  Messerschmitt Aktiengesellschaft, Augsburg

[1] Datasheet

 

[2] Rev.Increase

   

[3] -

     

[4] Power Curve & SFC: DB601A/B

       
         
           
           
           
         
       

-

     

Power Curve: DB601A1 (4000 m) [5]

   

Power Curve: DB601A1 (4500 m) [6]

 

Power Curve: DB601A1 (4500 m) [7]

Liquid cooled four-stroke Otto engine with direct fuel injection      DB 601A/B. type 1.

1, Description:     12-cylinder inverted Vee-engine
                    Volume     33,93 liter,     Fuel 87 octane
                    Propeller driven by reduction gear, flange shaft, 180 dimater       
                    Reduction gear ratio for    601 A:    1,55 : 1
                                                601 B:    1,88 : 1
                    Rotation of the propller:   left (seen from the
                                             power  transition side DIN 9001)

                    Single stage supercharger with stageless, controllable supercharger drive
                    Mechanical mixture enrichment at 1' (110%) output

2. Dimensions:      Lenght 1852 mm from the propeller flange shaft to and
                                   including the electric starter

                           1722 mm from the propeller flange shaft to the
                                   rear of the supercharger housing


                    Width        739 mm
                    Height       1027 mm

3. Weight:          RLM unit weight:                610 kg + 3%
                    (without clearance)

4. Performance, revolutions, fuel consumption, flying altitude:

                    Near ground level:         PS       revs/min      gr/PSh

     0 km           Incr. brief output  (1')  1100       2400        250/270
     0 km           Brief output        (5')   990       2400        220/232
     0 km           Incr. cont. output (30')   910       2300        220/232
     0 km           Max. cont. output          810       2200        220/232

                    Near rated altiude:        PS       revs/min      gr/PSh

     4.5  km        Brief output        (5')  1020       2400 incre- 220/232
                                                       sable to 2800
     4.5  km        Incr. cont. output (30')   960       2300        220/232
     5.0  km        Incr. cont. output (30')   960       2400        220/232
     4.88 km        Max. cont. output          860       2200        220/232
     5.7  km        Max. cont. output          890       2400        230/242
     5.5  km        Cruising output          ~ 800       2200        210/222
                    Barometric control of the supercharger RPM from 2.1 km

5.Heat dissipation: Coolant heat ~ 305 kcal/PSh at rated altitude at 2400n (5'-rat.)
                    Lubricant heat ~28     ""   near ground level at 2400n (5'-rat.)
                    Lubricant heat ~24.5   ""   at rated altitude at 2400n (5'-rat.)

6. Propeller:       VDM propeller w. external pitch mechanism and control unit,
                    Installation of the electro-mechanical automatic pitch control is possible.
7. Weapons:         2 connector for single or double forks; Installation of engine
                    cannon ispossible.
8. Fuel system:     Seperate fuel pumps in the machinery section
9. Coolant system:  Closed (max. 0.75 atü) coolant cross-circulation with coolant
                    tank in the main or aux. electric circuit
10. Sparkplugs:     Normal
11: Misc:           Output figures are understood for
                    The 2800 rpm is to be flown only with Automatic override ON
                    and above the rated altitude
12. Development:    In serial production.

___________