JF17 Thunder's New More potent superior Engine

[AZADPAKISTAN2009]

Guizhou WS-13

The People's Republic of China began development of the turbofan in 2000, taking into consideration that Russia may cave into Indian pressure and not allow the Klimov RD-93-powered JF-17 be exported to Pakistan. However, China moved on with the exportation, neglecting Indian protests, allowing the successful induction of the first JF-17 squadron in Pakistan on 18 February 2010. While initial production of the JF-17 will use RD-93 engines, later batches will be powered by the WS-13, which has 10% greater thrust, digital authority control system and solid titanium alloy fan blades.

The WS-13 Taishan was certified in 2007 and serial production began in 2009. An improved version of the Taishan providing a thrust of approximately 100 kN (22,450 lb) with afterburner is under development.

The 2010 March 18th edition of the HKB report stated that a FC-1 equipped with the WS-13 completed its first successful runway taxi test

OMG block 2 JF17 thunder already under development good stuff

Maximum thrust: 51.2 kN dry; 86.37 kN with afterburner
Turbine inlet temperature: 1650 K
Thrust-to-weight ratio: 7.8

Comparison withe Pratt & Whitny F16 C/D engines

Maximum thrust:

17,800 lbf (79.1 kN) military thrust
29,160 lbf (129.6 kN) with afterburner
Overall pressure ratio: 32:1
Specific fuel consumption:

Military thrust: 0.76 lb/(lbf·h) (77.5 kg/(kN·h))
Full afterburner: 1.94 lb/(lbf·h) (197.8 kg/(kN·h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)

 

[graphican]

Great News.. so Thrust-to-wait ratio is going to improve even further. Lovely!.

Now the next needed improvement is in Avionics. We need something that would take its performance to close to Falcon - Block-52 and that shouldn't be any distant either.

 

[AZADPAKISTAN2009]

Well with the new Advance Engine , with Afterburning capacity to be added , our JF17 Thunders probbly will be 15% more dangerous then what they were before.

The main thing is 100% self sufficiency in the engine technology with superior performance & quality not to mention Ability to Afterburn while in flight we are talking serious performance enhancements for the JF17 Thunder.....

An afterburner (or reheat) is an additional component added to some jet engines, primarily those on military supersonic aircraft. Its purpose is to provide a temporary increase in thrust, both for supersonic flight and for takeoff (as the high wing loading typical of supersonic aircraft designs means that take-off speed is very high). On military aircraft the extra thrust is also useful for combat situations. This is achieved by injecting additional fuel into the jet pipe downstream of (i.e. after) the turbine.

Now those escaping fighter planes can't escape with these enhaced engines

Together with the AESA reseach in China & advance avionocs boy oh boy the Thunder project will become a monster

Also if we sell the JF17 thunders to customer 100% of profit split between China and Pakistan !!! what a great situation 5,000,000 USD more for avionics research and development per plane sale

Block 2 JF17 thunder , on time ...

Well the engines are now in fine tweek phase , performance enhancement , chinese quality assurance so its a small proess but we can wait untill we have 70 JF17 thunder etc in 1 year but the engines are ready to go .....already being tested on prototype
JF17 thunders in china

 

[Nishan_101]

Thats quite a good news and even better for us and we should now have our own production line of it, try to return back to russia or sell those engines to Syria or Yemen.

 

[Areesh]

Thats quite a good news and even better for us and we should now have our own production line of it, try to return back to russia or sell those engines to Syria or Yemen.

No keep those engines for spares.

 

[WAQAS119]

I want to see TVC engine for JF17......

 

[bd_4_ever]

The 2010 March 18th edition of the HKB report stated that a FC-1 equipped with the WS-13 completed its first successful runway taxi test

So by when are we seeing these engines in JF-17....?? Test was successfull, hence i believe it wont be long....can anyone shed some light pls....

I came over a news that our BAF is taking JF-17 into serious consideration....but i dont know which versions will we be going for....


Cheers!!!

 

[fatman17]

aray bhai, RD-93 aur WS-13 both will be available to pakistan - dont worry!!!

 

[mughaljee]

Brother's
are we involve in the "Manufacturing" of WS-13 ?

 

[Areesh]

aray bhai, RD-93 aur WS-13 both will be available to pakistan - dont worry!!!

Yeah just another rumor like that french avionics deal rumor spread by some dil jalai.

PAF answer to all such people is mehnat kar hasad na kar.

 

[Crypto]

Excellent news! extra thrust will make thunder go Zoom Zoom
Any news on the turbine blades issue?

 

[Imran Khan]

go thunder go we will see you after 3 years a really working horse

 

[hataf]

so all in all you are saying that JF-17 will be pain in @$$ of many air craft manufacturing countries ........



so after that what will be the responce by

USA
FRANCE
RUSSIA
...........
..........
..........

 

[Manticore]

The WS-13

Maximum thrust: 51.2 kN dry;
86.37 kN with afterburner
Turbine inlet temperature: 1650 K
Thrust-to-weight ratio: 7.8

Comparison withe Pratt & Whitny F16 C/D engines

Maximum thrust:

17,800 lbf (79.1 kN) military thrust
29,160 lbf (129.6 kN) with afterburner
Overall pressure ratio: 32:1
Specific fuel consumption:

Military thrust: 0.76 lb/(lbf·h) (77.5 kg/(kN·h))
Full afterburner: 1.94 lb/(lbf·h) (197.8 kg/(kN·h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)

WS-10A
* Dry weight: 1494 kg
* Compressor: 3 fan and 9 compressor stages
* Bypass ratio: ~0.78:1
* Turbine: 1 high-pressure and 2 low pressure stages
* Maximum thrust: 132 kN with afterburner
* Turbine inlet temperature: 1750 K
* Thrust-to-weight ratio: 7.5




RD-33
* Type: Afterburning Turbofan
* Dry weight: 1,055 kg (2,326 lb)
* Maximum thrust: 50.0 kN (11,230 lbf) Dry, 81.3 kN (18,285 lbf) Afterburning
* Specific fuel consumption: 75 kg/(kN·h) (0.77 lb/(lbf·h)) dry, 188 kg/(kN·h) (1.85 lb/(lbf·h))
* Thrust-to-weight ratio: 4.82:1 (dry), 7.9:1 (afterburning)

F404-GE-402
# Type: Afterburning turbofan
Dry weight: 2,282 lb (1,036 kg)
* Maximum thrust:
o 11,000 lbf (48.9 kN) military thrust
o 17,700 lbf (78.7 kN) with afterburner
o Overall pressure ratio: 26:1
o Specific fuel consumption:
o Military thrust: 0.81 lb/(lbf·h) (82.6 kg/(kN·h))
o Full afterburner: 1.74 lb/(lbf·h) (177.5 kg/(kN·h))
o Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)


Snecma M88
Type: Twin-shaft, bypass turbofan engine
Dry weight: 897 kg (1,978 lb)
* Maximum thrust:
o 11,250 lbf (50.04 kN) military thrust
o 17,000 lbf (75.62 kN) with afterburner
o Overall pressure ratio: 24.5:1
o Turbine inlet temperature: 1,850K (2,871 °F)
o Fuel consumption: dry 0.80 kg/(daN·h)
o Thrust-to-weight ratio: approx. 8.5:1


Eurojet EJ200
# Type: Turbofan
Dry weight: 2,180 lbs (989 kg)
* Maximum thrust: 13,500 lbf (60 kN) dry thrust / 20,000 lbf (90 kN) with reheat
* Bypass ratio: 0.4:1
* Overall pressure ratio: 26:1
* Specific fuel consumption: 21-23 g/kNs dry thrust / 47-49 g/kNs with reheat
* Thrust-to-weight ratio: 9.175:1


WS-13 which offers Thrust of 51.2 kN dry and 86.37 kN with afterburner.


RD-33 basic offers 81.4KN
RD-33 Upgraded(3M Series version) offers 86KN (For SMT)
RD-33K offers 92.2KN( ALready For Mig29K of indians)
RD-43 offers 98.1KN( For SMT-II / M1/M2)
RD-33-10M offes 103KN will beinstalled in the Advance MiG-29 the prototype for the108KN(23350lb)- 117.7-kN (26,450-Ib) VK-10M engine

 

[QADRI]

thnks to russia for stoping RD-93 to Pakistan...atleast now we will have something more powerfull then that of before.