Talk:Pratt & Whitney F135

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Aviation: Engines

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Fuel used for this engine

I've been trying to find out what fuel is used in the F-35B engine and I've not had much luck. I've heard both JP-5 and JP-8 but no search seems to come up with a result. They talk about thrust & weight but never about fuel type. Is there a source I'm missing and shouldn't it be either on the engine page or the F-35 page? CycloneSteve (talk) 03:31, 20 December 2023 (UTC)[reply]

The popular answer seems to be JP-8/F-34 which is supported by this photo of an F-35 being refuelled. Fuel type is a parameter of Template:Jetspecs but it's only meant for generic Avgas/Avtur types apart from a few exceptions that use exotic fuel like JP-7. One reason that fuel types are not generally listed in aircraft or aircraft engine articles even when known is that it could break WP:NOTGUIDE/WP:NOTMANUAL, we don't want ground crews and pilots checking Wikipedia for servicing their aircraft! Nimbus (Cumulus nimbus floats by) 15:00, 20 December 2023 (UTC)[reply]

Engine weight and thrust-to-weight ratio under American standard and Russian/Chinese standard

As far as I know, the Russian and Chinese standard engine weight does not include the nozzle and control system, so when calculating the engine weight and thrust-to-weight ratio, they should be calculated in two cases: the American standard and the Russian(Chinese) standard.

This is why many Chinese sources say that F119 has a thrust-to-weight ratio of 9+ but current entry of the F119 states that the thrust-to-weight ratio of the F119 is just 7.0 .

Their is another way to prove my point of view. Su-35 weighs 19t and max thrust of AL-41F-1S is 14t. F-35A weighs 13.3t,and max thrust of F135 is 19.5t. The thrust-to-weight ratio of Al-41 is 8.8 and that of F135 is just 6.7 under the current entries. But the thrust-to-weight ratio of Su-35 is JUST 2×14÷19≈1.47，and that of F-35A is 1×19.5÷13.3≈1.47. This may be caused by the difference in engine weight standards between the two sides.

Improvements to current F135 entry:

We already know the weight of the YF119-PW-100L prototype without the divergent nozzle section is approximately 3,900 lb, and Pratt & Whitney's brochure clearly stated that the F135 weighs 1,500 pounds more than the F119. So the weight of the F135 is approximately 3900+1500=5400lb Russian/Chinese standard.

Considering that the engine weight and the thrust-to-weight ratio in the AL31 entry clearly cited Russian sources, engine weight and thrust-to-weight ratio of the F135 under Russian standard（Chinese standard）should be listed in addition. 湾岸2024 (talk) 15:37, 18 December 2024 (UTC)[reply]

If I understand correctly you are describing personal analysis and synthesis of sources to arrive at some unpublished values? That is not going to happen. The only 'standards' applied to Wikipedia engine articles is that appropriate measurement systems are used (Imperial, SI, Metric) and that the values come from a reliable source. Wikipedia is a general encyclopedia. Nimbus (Cumulus nimbus floats by) 16:11, 18 December 2024 (UTC)[reply]

For example, many reliable Chinese literature consider F119 to have a thrust-to-weight ratio of 9.0+, which is not the same as the value given in the original entry. Which one should be selected when editing the entry？湾岸2024 (talk) 17:04, 18 December 2024 (UTC)[reply]

Those Chinese literature have been published in various journals and is publicly available. 湾岸2024 (talk) 17:08, 18 December 2024 (UTC)[reply]

Some English sources also give different ratio. 湾岸2024 (talk) 17:13, 18 December 2024 (UTC)[reply]

Source

F-35 Lightning II,Mark Ayton,Key Publishing Ltd,https://www.scribd.com/document/545351245/F-35-Lightning-II Please add this 湾岸2024 (talk) 18:53, 18 December 2024 (UTC)[reply]

Source is not accessible, requires sign up to Scribd.com. Also states clearly that it is AI-enhanced. Nimbus (Cumulus nimbus floats by) 19:14, 18 December 2024 (UTC)[reply]