Can Volvo RM-12 Jet Engine Replace Thunder's RD-93 ?`

[IceCold]

With the increase in composite materials in the latter blocks, the weight of the JF-17 can be reduced which means it can be pushed beyond mach 2 or atleast to mach 2. Engine has nothing to do with it. RD-93 has sufficient thrust.

 

[AZADPAKISTAN2009]

I mean it would be interesting option no doubt but we will let chinese decide on that matter we would love to learn and develop the engines of fighters a bit more locally hopefully as years progress to gain some expertiese

 

[SBD-3]

Hello all:

As you all know that Chinese Company Geely Automobiles has bought out Swedish Volvo & Volvo Aero is its Subsidary which manufectures RM-12 Turbofan Jet Engine which is the Powerplant for JAS-39 Gripen Fighter jet.

RM-12 is a derivative of GE-404 which is the powerplant for F-18 hornet.

By China having as the owner of the Company can they award a contract along with GE to CAC & PAC to power JF-17 Thunder with this Engine ?

Specs

General characteristics

Type: Afterburning turbofan
Length: 154 in (3,912 mm)
Diameter: 35 in (889 mm)
Dry weight: 2,282 lb (1,036 kg)
Components

Compressor: Axial compressor with 3 fan and 7 compressor stages
Bypass ratio: 0.34:1
Turbine: 1 low-pressure and 1 high-pressure stage
Performance
Maximum thrust:

11,000 lbf (48.9 kN) military thrust
17,700 lbf (78.7 kN) with afterburner
Overall pressure ratio: 26:1

Specific fuel consumption:

Military thrust: 0.81 lb/(lbf·h) (82.6 kg/(kN·h))
Full afterburner: 1.74 lb/(lbf·h) (177.5 kg/(kN·h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)

It will also Imrove thunder's speed (Possibly from current Mach 1.8 to Mach 2) and payload capacity .

Share your Ideas Please.

Regards: BB

IMHO, geely has only acquired the commercial business arm of Volvo (i.e Volvo motors, renault volvo) not the Volvo Aero. Sweedish Govt would not have allowed such a deal which would potentially allowed China to access critical engine technology..furthermore, Volvo will continue working from sweeden...the news indicate

 

[Kompromat]

It's not always about the engine, look at the Mirage F-1 it's engine is extreemly weak (13,240 lbf) with afterburner but it is able to acheive mach 2.3.

But what are the other Factors ?

 

[Dazzler]

Speed is not just related to engine power but on several other factors such as airframe strength etc. If only engine power was enough to gain speed, the JSF would have been crossing mach 2 on regular basis which is not. So is the case of Raptor which has very powerful turbofan engines developed for any American fighter aircraft till date. Also, the F-7's turbojet engine peaks at meager 64 kn with after burner and yet it achieves mach 2+.

RM-12 is not a possibility by any chance and is not even considered as feasible for Thunder as it has one too many strings attached and is also under powered. RD-93 is a very good engine as it has proved during stiff trials and performances time and again. Its response time is excellent and is virtually as responsive to the aircraft as the aircraft is to the pilot commands via Digital FBW off course.

 

[ptldM3]

But what are the other Factors ?

There are several factors but i will start with wing thickness, thiner wings reduce drag, thus giving the aircraft better efficiency, the downside of a thin wing design is the problem of fuel storage. Think of the F-104, it acheived its speeds due to the thin wing design.

F-104 Starfighter - Wikipedia, the free encyclopedia

The F-104 featured a radical wing design. Most jet fighters of the period used a swept-wing or delta-wing planform. This allowed a reasonable balance between aerodynamic performance, lift, and internal space for fuel and equipment. Lockheed's tests, however, determined that the most efficient shape for high-speed, supersonic flight was a very small, straight, mid-mounted, trapezoidal wing. The new wing design was extremely thin

A more practical solution is a swept wing or increasing a wings angle or sweep, doing this does several things; firstly by having a swept wing design the drag is generally reduced. Moreover, a swept wing in a way acts like a thin wing design.

Untitled Document

Swept wings are used on aircraft not only to increase stability and the pilots view, but they also allow the plane to fly at much higher speeds. By placing the wings at an angle of 30 or 40 degrees, the critical Mach number can be increased, decreasing the drag and delaying or preventing shock stall. Shock stall is caused by the center of pressure moving backwards, interferes with the boundary layer and causes the plane to vibrate.

Wave drag - Wikipedia, the free encyclopedia

Sweeping the wing to the rear makes it appear thinner and longer in the direction of the airflow.

There are several different types of 'drag' and the 'wing span-to-chord ratio' among other factors play a role in the way an aircraft performes, be it at high speeds, slow speed or extreem angles of attack. wing span-to-chord ratio or basically the general design of the wing determines many things including drag, but the most important design features in a wing (if you want greatest airspeed) is the wing sweep and thickness.

Lets look at drag or more specifically wave drag, 'the Haack body' is most effective in countering the phenomenon of wave drag, a delt-wing would best represent the Haack body, some aircraft that are able to acheive a realatively fast cruise speed work on the principle of the Haack body, thus wave drag is significantly reduced.

Sears?Haack body - Wikipedia, the free encyclopedia

The Haack body is, generally speaking, the body least susceptible to wave drag. By Frenzl's Area Rule, the derivative of cross-sectional area gives wave drag. Thus, the Haack body is pointed at two ends and grows to a maximum and then decreases toward the second point.

Under the area rule, shapes with the same cross-sectional area at each point along their length as this shape have the minimal amount of wave drag, and the overall shape of many aircraft designed with transonic flight considerations have cross-sectional areas that approach this form (despite appearances).

 

[Kompromat]

Thanks Russki and Nabil

 

[AZADPAKISTAN2009]

Perhaps this could be used in a future collaboration project we can use this engine in some capacity it looks fantastic


Is there any active plane /fighter that uses this engine platform ?

 

[hataf]

sorry little off topic
what is expected decrease in weight of jf-17 by using composit material
put every thing a side
will it give any technical information about development of engine to chinees

 

[hataf]

But what are the other Factors ?

the surface area is very less mean less drag mean high speed

 

[Kompromat]

Hearing some rumors about the Success of WS-13

 

[hataf]

Hearing some rumors about the Success of WS-13

what are specs of ws-13

 

[Kompromat]

what are specs of ws-13

100KTN of Thurst is something significant

 

[Dark Angel]

100KTN of Thurst is something significant

Maximum thrust: 51.2 kN dry 86.37 kN with afterburner

 

[Kompromat]

^ I will try getting the source and post it.