RB211-524G/H-T
 

Hey all,

Just 2 quick questions with regard to the RB211-524G/H-T engine. Having studied the left hand side of the IP/LP turbine case, there seems to be what looks like a TCC (Turbine Case Cooling) inlet. The first question is, could someone please corroborate this? I know that the earlier RB211-535E4 engine, has an IPT TCC inlet located on its turbine case that is fed with bypass air. The cold air is then fed to the TCC inlet via ducting on the underside of the C duct reverser half to control case expansion and subsequent blade tip clearances.

My second question therefore is, due to the fact that the 524G/H-T doesn't incorporate 2 C duct reverser halves (it's 1 unit), from where would the bypass air be collected from and how would that air be ducted to the TCC inlet?

Many thanks folks!

All that glitters isn't gold !
The scoop/duct you see, (which is also duplicated on the R/H side) feeds air into the "interservices" area. This air cools the area but the main reason for this air is to feed the "Fan Air Metering Valve" which directs air to the pre-cooler, which cools the engine bleed air before being delivered to the airframe.

The RB211-524G/H-T has no external Turbine Case Cooling system, valves or ducting. There is no "case cooling" as such although Mr Rolls and Royce were smart enough to design internal cooling of turbine discs/blades with the appropriate cooling air being channelled via internal passages including the LP and IP drive shafts.

As there is no case cooling on the G/H-T this question is surperfluous !

:ok:

When we talk about TCC we usually mean valves and ducts which direct air onto the turbine case. No RB211 has any of this. So what is the IPT TCC on the 535?