Easily its most ambitious non-military aerospace endeavour, India has announced a competition to engine its proposed 90-seater indigenous regional jet, currently being conceptualised under the National Civil Aircraft Development (NCAD) programme under a cluster of civil and military laboratories.
The request for information put out by the National Aerospace Laboratory (NAL) requires responses by February 14, and is understood to have endorsed its RFI to all major engine vendors, including GE, Rolls-Royce and Pratt & Whitney. The RFI provides some interesting prospective figures though. “Present estimates show that such an engine will be required around 2017 time frame,” says the published RFI.
The NCAD project needs 40-80kN turbofans in a twin configuration, with a committed delivery of 20 engines in 2017 (when engine integration will presumably take place). Subsequently, according to the document, the project requires 1,000 engine sets at a rate of 80 each year spread over 20 years.
Doesn't the Kaveri Engine fit the Bill ? Unless I am missing something.
Why don't they begin hunt For Indian Civil Jet ? Either way each part will be sourced from abroad with a thiranga flourish painted on in the end….
India really needs to develop it's own aircraft engine as a priority
Kaveri engine needs a little more time to develop fully, probably 3 years time
Here we go!!! Another clusterf**k in the making.
If I'm correct, the kaveri engine is a low bypass ratio turbo jet engine, while the requirement for the civil aircraft will be a high bypass ratio turbo fan engine, and that we presently do not have…
Why don't they use dry version of Kaveri engine in present form and develop larger version with more dry thrust. They can generate more money where they can hire few academicians who were actively involved in cutting edge technology and pay them huge salary package and give them bonus for completing the technology goals. There should be an expert in material sciences , gas turbine , brisk design , combustor and after burner technology then only a useful workable engine can be developed . Just making expensive contracts would lead you nowhere. The 50 plus dry thrust engine can be used in 60 sweater and 75 plus dry thrust engine be developed for 100 sweater engine and these can further be developed for fighter aircraft. Rafale Snecma engine is obsolete technology and no one would give that technology and GTRE cannot deliver it obits own so develop it with consultants who have significant achievements as by 2020 there would be huge demand for civilian aircraft and due to lack of planning india would spend large amount of foreign exchange to buy that and further evaluate the currency.The smart government understands the needs and plans the action. The Saras is very slowly progressing and there is very minimal contribution to civilian aviation and look at Brazil as to where they stand today.
This project was initiated circa early 2000s. It may be a coincidence that it coincided with the first batch of retirees from ADA. It may also be a sinecure for the "privileged".
After 12-13 years someone has woken up to the fact thaqt this thing needs an Engine.
Sometime s I feel someone is trying to break my heart.
Technology Submission – Novel Rotary-Turbo-InFlow Tech – Featured Development
GEARTURBINE PROJECT
Atypical InFlow Thermodynamic
Technology Proposal Submission
Novel Fueled Motor Engine Type
*State of the art Innovative concept Top system Higher efficient percent.
Have similar system of the Aeolipile Heron Steam device from Alexandria 10-70 AD. -New Form-Function Motor-Engine Device. Next Step, Epic Design Change, Broken-Seal Revelation. -Desirable Power-Plant Innovation.
http://www.youtube.com/watch?v=0cPo9Lf44TE
YouTube; * Atypical New • GEARTURBINE / Retrodynamic = DextroRPM VS LevoInFlow + Ying Yang Thrust Way Type – Non Waste Looses
-This innovative concept consists of hull and core where are held all 8 bteps of the work-flow which make the concept functional. The core has several gears and turbines which are responsible for these 8 steps (5 of them are dedicated to the turbo stages). The first step is fuel compression, followed by 2 cold turbo levels. The fourth step is where the fuel starts burning – combustion stage, which creates thrust for the next, 5th step – thrust step, which provides power to the planetary gears and turbines and moves the system. This step is followed by two hot turbo steps and the circle is enclosed by the final 8th step – bigger turbine. All this motion in a retrodynamic circumstance effect, wich is plus higher RPM speed by self motion. The Reaction at front of the action.
*8-X/Y Thermodynamic CYCLE – Way Steps:
1)1-Compression / bigger
2)2-Turbo 1 cold
3)2-Turbo 2 cold
4)2-Combustion – circular motion flames / opposites
5)2-Thrust – single turbo & planetary gears / ying yang
6)2-Turbo 2 hot
7)2-Turbo 1 hot
8)1-Turbine / bigger
-With Retrodynamic Dextrogiro vs Levogiro Phenomenon Effect. / Rotor-RPM VS InFlow / front to front; "Collision-Interaction Type" – inflow vs blades-gear-move. Technical unique dynamic innovative motion mode. [Retrodynamic Reaction = When the inflow have more velocity the rotor have more RPM Acceleration, with high (XY Position) Momentum] Which the internal flow (and rotor) duplicate its speed, when activated being in a rotor (and inflow) with [inverse] opposite Turns. A very strong Novel torque power concept.
-Non waste parasitic looses for; friction, cooling, lubrication & combustion. -Shape-Mass + Rotary-Motion = Inertia-Dynamic / Form-Function Wide [Flat] Cylindrical shape + positive dynamic rotary mass = continue Inertia kinetic positive tendency motion. Like a Flywheel.
-Combustion 2Two continue circular [Rockets] flames. [ying yang] opposite to the other. – With 2TWO very long distance INFLOW [inside propulsion] CONDUITS. -4 TURBOS Rotary Total Thrust-Power Regeneration Power System. -Mechanical direct 2two [Small] Planetary Gears at polar position. -Like the Ying Yang Symbol/Concept. -Wide out the Rotor circumference were have much more lever [HIGH Torque] POWER THRUST. -No blade erosion by sand & very low heat target signature profile. -3 points of power thrust; 1-flow way, 2-gear, 3-turbine. *Patent; Dic. 1991 IMPI Mexico #197187 All Rights Reserved. Carlos Barrera.