gogbot
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I don't know what the IAF is complaining about:
Kaveri:
Military thrust (throttled):11,687 lbf (52.0 kN)
Full afterburner:18,210 lbf (81.0 kN)
Klimov 93 (powers JF-17)
Maximum thrust: 50.0 kN (11,230 lbf) Dry,
Afterburner: 81.3 kN (18,285 lbf)
Am I missing something?
In mid-2004, the Kaveri failed its high-altitude tests in Russia, This unfortunate development led the Indian Ministry of Defence (MoD) to order 40 more IN20 engines in 2005 for the first 20 production aircraft, and to openly appeal for international participation in completing development of the Kaveri. In February 2006, the ADA awarded a contract to SNECMA for technical assistance in working out the Kaveri's problems. At that time, the DRDO had hoped to have the Kaveri engine ready for use on the Tejas by 2009-10.
Kaveri only showed positive progress , as of 2008
But by then The GE-404 engines were already purchased.
next year in 2009
Scientific Advisor to Defence Minister M Natarajan said nearly 90 to 93 per cent of the expected performance had been realised and the government had recently floated an expression of interest to seek partners to move the programme further
And only this year has a full 100% of the engine been realised.
With still some minor weight reduction problems between 50-60 kg
But the IAF has branded both the Ge-404 an underpowered engine .
And asked for a new engine according to these parameters.
Specifications (F414-400)
Data from General Electric
General characteristics
Type: Afterburning turbofan
Length: 154 in (3,912 mm)
Diameter: 35 in (889 mm)
Dry weight:
Components
Compressor: Axial compressor with 3 fan and 7 compressor stages
Turbine: 1 low-pressure and 1 high-pressure stage
Performance
Maximum thrust: 22,000 lbf (98 kN)
Overall pressure ratio: 30:1
Thrust-to-weight ratio: 9:1
Ej-2000
Specifications
Data from Rolls-Royce
General characteristics
Type: Turbofan
Length: 157 inches (4.0 m)
Diameter: 29 inches (0.737 m)
Dry weight: 2,180 lbs (989 kg)
Components
Compressor: 3-stage LP, 5-stage HP
Turbine: 1-stage LP, 1-stage HP
Performance
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
compared to Kaveri they are better.
Specification (GTX-35VS Kaveri)
General characteristics
Type: Afterburning turbofan
Length: 137.4 in (3490 mm)
Diameter: 35.8 in (910 mm)
Dry weight: 2,427 lb (1,100 kg) [Production model goal: 2,100 lb (950 kg)]
Components
Compressor: two-spool, with low-pressure (LP) and high-pressure (HP) axial compressors:
LP compressor with 3 fan stages and transonic blading
HP compressor with 6 stages, including variable inlet guide vanes and first two stators
Combustors: annular, with dump diffuser and air-blast fuel atomisers
Turbine: 1 LP stage and 1 HP stage
Performance
Maximum thrust:
Military thrust (throttled):11,687 lbf (52.0 kN)
Full afterburner:18,210 lbf (81.0 kN)
Specific fuel consumption:
Military thrust: 0.78 lb/(lbfh) (79.52 kg/(kN·h))
Full afterburner: 2.03 lb/(lbfh) (207.00 kg/(kN·h))
Thrust-to-weight ratio: 7.8:1 (76.0 N/kg)
If it had been ready earlier it may have seen more use but , sadly it's to late to catch the Tejas.
May be in latter Upgrades of the Tejas , a new Kaveri upgraded engine may be use but for now .
In September 2008, it was announced that the Kaveri would not be ready in time for the Tejas, and that an in-production powerplant would have to selected. Development of the Kaveri by the GTRE would continue for other future applications.
The DRDO, however, currently hopes to have the Kaveri engine ready for use on the Tejas by 2009-10. but according to latest news still research on it is going on and date to complete its research has been extended to 2011-2012.