TR Propulsion Systems

[Zafer]

TEI exported a sizable lot of engines.

https://twitter.com/i/web/status/2053095811852972217

 

[Yasar_TR]

According to the statements, we can say that the qualification for the TS1400 has been completed and customer requirements have been met. Regarding certification: First Stage is Design Verification. Theoretically proving that the engine's design and engineering calculations comply with civil aviation standards (EASA CS-E). Second Stage: Organizational Competence. Confirmation that the manufacturer (TEI) has the infrastructure and quality system to produce this engine with consistent quality every time.

Third Stage: Final Testing and Qualification. Proving that the engine, whose design and structure have been approved, has passed critical tests such as icing, bird strike, and 150-hour endurance tests in the presence of international auditors. At the end of this stage, the EASA CS-E airworthiness approval, civil passenger transport authorization, and the 'Type Certificate' critical for export are obtained.

In summary, the TS1400 is technically and militarily ready for duty, presumably. However, the international certification process for civilian tests focused on human life (and which could create export barriers) is ongoing. The timeline for the final, type certification might not be solely in TEI's hands. I don't want to speculate, but with the TS1400, TEI entering an important league that will be sharing the market with some traditional suppliers.

One thing we mustn’t overlook is the 56 piece order of Gokbey Navy has placed with Tusas. That means 120+ engines that are navalised as well as the helicopter it self. Also TS-1400 needs to be of military spec. Do we know if these parameters have been met.

 

[Strong AI]

Baykar will produce the TB2 engine in thousands. Baykar are alse working on a turbine engine inhause and are committed to success.

https://twitter.com/i/web/status/2053036424518070774

I can understand and i think it is good for Baykar to work on their own engines.
In the recent interview from Tolga Özbek with Mr. Akşit, it is stated TEI has neither time nor money to make engines for every kind of aircraft. I mean yes, they are working now on TF10000, but God knows when they can deliver first units for integration and testing. And for the aircraft itself it makes a difference if you want one big engine or two smaller engines to meet the required thrust. Because it affects its geometry and thus its RCS and dimensions of its IWB (also s-duct or y-duct, latter one leads to split IWB). Maybe Baykar came to the conclusion that one 20.000 lbf engine will be better for them instead of two 10.000 lbf. And looking back at that statement made by Mr. Akşit, in the future if Baykar knocks on the door of TEI with a different request, only God knows if TEI can start a new project to meet Baykar's requirements.

 

[HKY]

During the interview with Tolga Özbek when talking about TF6000 Mahmut Akşit said "This is a simplified, first version of the engine."

Many commentators said TF6000 is as big as F404 so it needs to have higher thrust . Hopefully much powerful versions (8000-10000 lbf) will arrive. A 10.000 lbf dry -16600 wet variant could easily power Hurjet or future Kızılelma variants.

 

[boredaf]

Many commentators said TF6000 is as big as F404

Who said that? It is more than a meter shorter, has something like 30 cm smaller diameter and weighs third what F404 does.

 

[Yasar_TR]

Let us look at them a little closer where it matters.

F404 fan diameter : ~28inches
TF6000 fan diameter : ~26 inches

F404 length : 391cm
TF10000 length : 315cm

F404 weight : 1035kg
TF6000 weight : ~400kg

Just because TF6000 looks fatter because it has a higher bypass ratio than F404, doesn’t make it a f404 class engine.
TF6000 has a 2inch smaller diameter fan. That governs the amount of air it can push in to the core.
But it has a much larger bypass ratio: 1.08:1 for tf6000
F404 bypass ratio : 0.34:1
For every 1kg of air going through tf6000’s core 1.08kg goes around it.
For every 1kg of air going through F404’s core, only 0.34kg of air goes around it.
As per Dr Aksit’s words; 40% of tf6000’s thrust comes from bypassed air.

Inspite of a smaller diameter fan, TF6000 pumps out a lot of air that bypasses the core for a 6000lbf class turbofan.

These are two very differently designed engines. TF6000 is designed with stealth in mind. It will perform better in lower altitudes. F404/is an all rounder. It is not stealthy as it is.

When Dr Aksit mentioned a “simpler” engine he didn’t mean tomorrow when the engine has matured it will give thrust levels like f404.
An increase of 10-15% can be expected as TEI works with a large tolerance level when designing engines if TS-1400 case is taken as a basis.

 

[Samba]

US: Hypersonic ramjet engine design time cut from months to seconds

The team at GE Aerospace said they simultaneously accounted for multiple flight conditions and scenarios for the hypersonic ramjet engine.

interestingengineering.com

 

[sh. Abdj]

Why many people in this forum are criticizing Gushhan Engine?! If Turkeye can make some changes on an engine that it knows how to produce abd make it more powerful with some structural changes it is enough work to call it new engine. In case the U.S did what it always do and tried to harm the project a ready engine is available.

 

[Saithan]

Let us look at them a little closer where it matters.

F404 fan diameter : ~28inches
TF6000 fan diameter : ~26 inches

F404 length : 391cm
TF10000 length : 315cm

F404 weight : 1035kg
TF6000 weight : ~400kg

Just because TF6000 looks fatter because it has a higher bypass ratio than F404, doesn’t make it a f404 class engine.
TF6000 has a 2inch smaller diameter fan. That governs the amount of air it can push in to the core.
But it has a much larger bypass ratio: 1.08:1 for tf6000
F404 bypass ratio : 0.34:1
For every 1kg of air going through tf6000’s core 1.08kg goes around it.
For every 1kg of air going through F404’s core, only 0.34kg of air goes around it.
As per Dr Aksit’s words; 40% of tf6000’s thrust comes from bypassed air.

Inspite of a smaller diameter fan, TF6000 pumps out a lot of air that bypasses the core for a 6000lbf class turbofan.

These are two very differently designed engines. TF6000 is designed with stealth in mind. It will perform better in lower altitudes. F404/is an all rounder. It is not stealthy as it is.

When Dr Aksit mentioned a “simpler” engine he didn’t mean tomorrow when the engine has matured it will give thrust levels like f404.
An increase of 10-15% can be expected as TEI works with a large tolerance level when designing engines if TS-1400 case is taken as a basis.

I like the explanation of how much air goes around the engine. But does that mean a lot more air goes around the engine that doesn't get used for thrust ?

My amateurish understanding tells me, the more air we can get to go into and through the engine the more thrust we would get.

So any air not going into the engine is wasted.