herky400M Posted August 7, 2015 Share Posted August 7, 2015 Can anyone explain to me the compressor power recuperation.As far as I know is the they put stage 1 blades or other blades futher back into the compressor...if the blades are reused how fast are they deteriorating? how hihg is the risk whenif they brake and create FOD in the compressor....if this is the case, than for how long does this compressor can go on, I expect less than an new one.when the blades are worn more quickly, the dimension of the inner compressor will become larger, so compressor discharge will be lesser...a lot of questionsPJ maybe you have a quick response to thisbest regards bob Quote Link to comment Share on other sites More sharing options...
pjvr99 Posted August 7, 2015 Share Posted August 7, 2015 This goes into the area of engineering and black magic. I will sit back and see if someone else has any idea Quote Link to comment Share on other sites More sharing options...
Fritz Wester Posted August 8, 2015 Share Posted August 8, 2015 You are referring to a process commonly called "blade cascading". This process is used for ground power engines ONLY and has never been approved for "flight" engines. The process relies on certain stages of the T56 series compressor blades that have the same dimensions other than length of the blade as measured from the root to tip. Blades that have the same dimensional "fit" other than or length can be cut "down" or shortened so they may be moved back and used in other higher stages of compression in the compressor. Again, "cascading" is not approved for flight engines. Quote Link to comment Share on other sites More sharing options...
herky400M Posted August 10, 2015 Author Share Posted August 10, 2015 Fritz, thx for the info. can you help find the document where it's stated that this is for industrial ground engines only...if anyone else has some ideas, please do send itbest regards bob Quote Link to comment Share on other sites More sharing options...
Fritz Wester Posted August 13, 2015 Share Posted August 13, 2015 I believe it is in the 501K industrial engine overhaul manual allowing cascading and which stages can be cascaded. As for the flight engines, nothing says you can't, BUT, nothing says you can either. This is where if the procedure is not in the manual providing instructions on how to do, it is not an approved procedure and therefore would not be allowed. I therefore must emphatically say, it is not an approved procedure or process for flight engines. Quote Link to comment Share on other sites More sharing options...
HercMX Posted August 14, 2015 Share Posted August 14, 2015 Think "density altitude"... The engine needs all the air it can get at altitude......... Jack Quote Link to comment Share on other sites More sharing options...
herky400M Posted August 21, 2015 Author Share Posted August 21, 2015 FW, without hard evidence or proof, it's hard to state this to our civilian company, until know we have 4 compressors where a blade was ripped of and damaged the rest of the compressor and turbine.. BR bob Quote Link to comment Share on other sites More sharing options...
Fritz Wester Posted August 22, 2015 Share Posted August 22, 2015 And thus the reason why I stated the "cascading" of blades is not approved for flight engines. The 501K is the "industrial" engine version of the T56/501 engine family. If a compressor eats a blade on an industrial engine, the resulting failure doesn't affect an aircraft, only the ground or shipboard equipment it is powering. My quote: "This is where if the procedure is not in the manual providing instructions on how to do, it is not an approved procedure and therefore would not be allowed. I therefore must emphatically say, it is not an approved procedure or process for flight engines." Quote Link to comment Share on other sites More sharing options...
herky400M Posted September 5, 2015 Author Share Posted September 5, 2015 FW, thanks for te-he reply, I'm convinced, but if I do not have any paper which says that this is not approved by FAA or EASA. Than in aviation you go no where.BR bob Quote Link to comment Share on other sites More sharing options...
larry myers Posted September 6, 2015 Share Posted September 6, 2015 (edited) ,Bob,Sounds to me like a case of the tail wagging the dog. Is your contractor applying pressure to accomplish compressor blade cascading on your Herk. T56 engines? If so, your his customer, so insist he provide you the written FAA/EASA guidance that permits the compressor maintenance it seems your contractor is advocating. I agree wholeheartedly with Fritz. Further, am surprised your contractor who is evidently a certified FAA/EASA company would, in good conscience, recommend a procedure meant only for engines operating in a nonflying environment. Do you have access to a Rolls Royce rep? Edited September 6, 2015 by larry myers Quote Link to comment Share on other sites More sharing options...
herky400M Posted October 12, 2015 Author Share Posted October 12, 2015 Larry, sorry it took awhile.No I don't have acces to a Rolls Royce rep. A few of my NCO's went to Indiana to follow o-level course T56. And they stated that blade cascading was no problem for the first 3 stages of the compressor.how can I get acces to the Rolls Royce rep?BEST REGARDS, Bob Quote Link to comment Share on other sites More sharing options...
howell fe Posted October 16, 2015 Share Posted October 16, 2015 Little Rock RR office: 501 986 4869. Can probably put you in touch with your regional rep. Quote Link to comment Share on other sites More sharing options...
Recommended Posts
Join the conversation
You can post now and register later. If you have an account, sign in now to post with your account.