GE Engine spool-up time

[donpizmeov2]

What's the spool-up time for the GE90-115B?

[barit1]

The cert regs define max spoolup time; F/I to 95% of TO < 8 seconds IIRC.

Has been true since sometime in a prior millenium. :rolleyes:

[HazelNuts39]

Since similar questions pop up in PPRuNe from time to time, it may be useful to recall that two requirements govern turbine engine acceleration times. The first is for the uninstalled engine, the second for the engine installed in the airplane, supplying bleed air and power for aircraft services:

Part 33 AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES
Subpart E--Design and Construction; Turbine Aircraft Engines
Sec. 33.73 Power or thrust response.

[The design and construction of the engine must enable an increase--
(a) (...)
(b) From the fixed minimum flight idle power lever position when provided, or if not provided, from not more than 15 percent of the rated takeoff power or thrust available to 95 percent rated takeoff power or thrust in not over 5 seconds. The 5-second power or thrust response must occur from a stabilized static condition using only the bleed air and accessories loads necessary to run the engine. This takeoff rating is specified by the applicant and need not include thrust augmentation.]Part 25 AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES
Subpart B--Flight
Performance
Sec. 25.119 Landing climb: All-engines-operating.

[In the landing configuration, the steady gradient of climb may not be less than 3.2 percent, with the engines at the power or thrust that is available 8 seconds after initiation of movement of the power or thrust controls from the minimum flight idle to the go-around power or thrust setting--
(a) In non-icing conditions, with a climb speed of VREF determined in accordance with Sec. 25.125(b)(2)(i); and
(b) In icing conditions with the landing ice accretion defined in appendix C, and with a climb speed of VREF determined in accordance with Sec. 25.125(b)(2)(ii).]

[donpizmeov2]

Has been true since sometime in a prior millenium.

True and technology has improved quite a bit since the French Revolution, isn't it!

The real performance usually might be a bit better than the certification requirements ... despite the costs!

[lomapaseo]

True and technology has improved quite a bit since the French Revolution, isn't it!

The real performance usually might be a bit better than the certification requirements ... despite the costs!True and technology has improved quite a bit since the French Revolution, isn't it!

The real performance usually might be a bit better than the certification requirements ... despite the costs!


Cost doesn't enter into it.

Technology does control this. Choices, choices.

Safe thrust (free from engines stall/surges) need be managed by an accel rate dictated by the FADECs (etc.)

Neat job to manage the work between multiple spools as their inertias are quite different.

[donpizmeov2]

Cost doesn't enter into it.

Cost enters in every phases of flight, but it's an other story!


Technology does control this. Choices, choices.

True as a general rules but when you decide where to go if you don't have technology to support your decision you won't be able to build carbon fiber titanium blade with a reliability more than 15 years and 22 million flight hours!

[barit1]

I have seen demos wherein the spool-up time was dramatically shortened, perhaps as much as 50%.

But whether this type of response is desirable is another issue. Pitch-up in a modern airliner (underwing engines) might be an unpleasant surprise.

Further, the peak turbine temperature presents a parts life / cost problem that few would welcome.