Multi spline couplings (spline coupling, examples in Lit. 23.2.2-6 up to Lit 23.2.2-8) are the
typical shaft connection in accessory drives
of aeroengines. Also shafts of main rotors are joined with this
type of coupling (example 23.2.2-1). These enable a solid connection at the smallest space. Thereby the
shank of the shaft will be slided into an according `hollow' multi spline profile. Such a connection allows
axial movements and with this, the compensation of thermal expansions. Basically it must
reckoned with micro movements at the load transferring spline
flanges. They develop from small misalignments
or bending of the shaft. This causes fretting
(vibration wear, volume 2, Ill. 6.1-4). It must be minimized
with suitable measures at a tolerable size. This demands a permanent sufficient lubrication. Lubricates the
fuel itself, fuel pumps and control units act at
exspecially demanding conditions (Ill. 22.2-16,
example 23.2.2-2). For the designer it is a demanding task to guarantee the lubrication at any time. In
many seemingly inferior or uncritical cases, leaking oil from
seals adopts this task. According to the
requirement to avoid even minimum oil exit at aeroengines seals are further optimised. So the oil, needed for
lubrication of the coupling, lacks. In such a case it comes, not until a longer operation time, to a dangerous wear at
the multi spline toothing (Ill. 23.2.2-1 up to Ill. 23.2.2-4). In an extreme case the toothing is fully abraded
and the connection fails (volume 2, Ill. 6.2-18 and Ill. 6.2-19). If not till this the problem gets known,
extensive costly measures must be expected.
In connection with the wear a further problem can arise during exchange of the shaft. Such a situation is thinkable also during the exchange of an accessory device like a generator. During markedly wear, the contact of the bearing flanks of the splin toothening is no more optimal. This may be caused by the changed position and/or different wear. It comes to dangerous stress peaks, caused from locally concentrated load transfer, notch effect and type of loading (bending, torsion). Additionally the wear at the contact surfaces accelerates. This can lead to vibration fatigue overload at a predetermined rated breaking point. This is usually located in the shaft near the spline toothening. With this, the early failure of the shaft coupling gets more probably. Further potential secondary failures are failures of anti friction bearings and seals of the concerned shaft.
Ill. 23.2.2-1 (Lit.23.2.2-1): Shaft couplings with multi splines
are frequently used and are proven in gas turbines, especially in derivates. A big advantage is the
easy assembly by pushing together. That benefits the assembly /disassembly of accessories like generators, control units and pumps. In spite
of those advantages, multi splines are under unfavorable operation conditions also a potential
weak point. They are primarily exposed to fretting
(sliding wear). This leads to an abrasion of the
loaded flank. In an extreme case, it comes to the fracture of the remaining tooth cross section and so to
the failing of the coupling.
To prevent failures, an adequate lubrication is of great importance. It should be adjusted to the application.
According to the lubrication, additional the
materials combination of the contacting coupling
teeth can be of essential significance for the wear behavior. This is to keep in mind, especially for
repair coatings. If the coating in any way (e.g., pre-treatment product, deposit process) differs from
specifications in the manuals, the OEM must be consulted. In case of doubt
appropriate proofs are inevitable. Those require, as typical for wear processes, the
The existent type of wear is, not without cause, labeled as wear corrosion (fretting corrosion). The corrosion influence has great importance for the formation of the wear (abrasion) oxides. As electrolyte it comes into consideration primarily in marine atmosphere, respectively in the stand still, with sea salt contaminated condensate. The fine metallic abrasion is during formation chemically very active. It responses especially to oxidizing and corrosive influences.
Besides the lubrication conditions, the micro movements between the contacting tooth flanks play an important roll. They can have different causes, that can also act in combination:
Causes for the crack formation in multi spline couplings are probably:
Ill. 23.2.2-2 (Lit. 23.2.2 -3): Concerned is a typical case of a disimprovement. It arises indeed
only indirect in connection with the aeroengine, but is
for multi spline couplings extremely
Few minutes before the accident witnesses observed, that the airplane flew with about 30-60 meters hight noticeable low. Suddenly a small smoke plume formed. The aircraft rolled to the left till the wings stood vertical. Then the nose of the airplane tilted downward. The aurplane hit the runway and was destroyed. The examination of the components from the left propeller showed, that the blades have been only 3° actuated, instead the dialed ca. 80°. This adjustment didn't correlate the position of the propeller adjusting spindle, poiting at an inner problem.
A following investigation of the causative concerned aeroengine showed:
The shafts of the propeller control unit (= PCU) and the propeller run concentric (sketch in the middle). PCU and propeller are connected with the oil bearing transmission tube, which runs through the propeller shaft. The torque is transferred from the outer spline toothing of the transmission tube to the multi spline coupling of the inner transmission tube from the ball spindle. So, by a spindle, the propeller is actuated.
The transmission tube has on the spline toothing to the ball spindle, instead of the previous nitriding layer, a new introduced titanium nitride coating. Its surfaces appeared dull. This can be traced back to an increased roughness. It was no alarming wear.
In contrast, the spline toothings in the PCU spindles of both aeroengines showed heavy wear. In the left aeroengine the spline toothing was almost removed (sketch below right). So the coupling parts could rotate free against each other. With this an actuating of the propeller was no more possible.
Change of the surface treatment from the outer spline toothing of the transmission:
The old version with nitriding layer had no problems. Anyway the surface treatment was changed, to facilitate the production. The nitriding layer had to be reworked after removing the epsilon layer and straightening (distortion during nitriding).
An „improvement“ with a titanium nitride coating was carried out in a product improvement program. The distortion during the old process and with this the straightening could be avoided, due to the lower coating temperature of the titanium nitride. The experiences of the producer let expect a 3-4 times lower wear in comparison to the old coating version. Comparable applications seemed to reassure this. Because of the low toothing load, the wear behaviour was evaluated as second-rank.
Test runs with the propeller actuation have been carried out with an other aeroengine type. After this the coupling teeth showed shiny golden, typical for not deteriorated titanium nitride. This finding should have shown, that the test of the wear behaviour of the coupling teeth with a different aeroengine type was insufficient.
The heavy wear of the teeth in the ball coupling was later traced back at the high hardness difference to the titanium nitride coating on the teeth of the transmission tube. The very thin and hard TiN layer could not adjust the unevenness of the tooth flanks, as it was acceptable for the former nitriding layer. Because the roughness requirements have not been adapted, the TiNlayer acted as a rasp.
Ill. 23.2.2-3 (Lit. 23.2.2 -4 up to -6): During rolling to the start, the right aeroengine
accelerated autonomous. The associated warning light of a
too high exhaust gas temperature flashed. In spite
the withdrawal of the thrust, the warning light diaplayed further high thrust. All
trials to decrease the thrust failed. The aircraft came damaged to rest on the runway. It was afterwards destroyed by a
fire after a successful evacuation.
The following investigation of the dismounted fuel pump and the fuel control unit showed:
Control unit and pump are connect by a shaft with a multispline coupling at each side (sketch below left). Its rotational speed is proportional high pressure shaft/rotor (N2 ). On the side of the control unit the spline toothing showed no wear at all. However the toothing at the side of the pump was nearly gone. So the parts could rotate free to each other. With this, the measuring of the rotation speed was no more possible. Even a partly loss of the N2 signal is interpreted by the control unit as a demand to rise the speed again with an increased fuel supply. The only possibility against too high rotation speeds and exhaust gas temperatures is the cut off of the fuel. This is also possible with the „fire lever”.
Already 20 years before the accident, several toothing failures occurred at control unit shafts. These failures have been traced back to alignment failures. To clear the failure cause, at that time the producer of the pump carried out tests. These showed, that the torque at the shaft caused the misalignment (sketch below right) at the side of the pump. As remedy an axial offset was introduced with several service bulletins. How this measure avoided the wear can not be seen from the papers on hand.
In spite of this measure, in the last years according to the OEM about 40 similar cases of wear occurred. The aircraft OEM reports about further 26, also at other aircraft types (Ill. 23.2.2-4) with the same pump/control unit configuration. Even parts, which have been already changed during production, showed susceptible for wear.
There where drop outs at all flight situations like start, climb, cruise, descent and approach. A causative influence is attributed to misalignments.
There exists no fix inspection interval. Therefore several operators define these themselves. However usually a repair takes place only after a malfunction.
Some months after the accident; with a service bulletin a new shaft version is introduced. It consists of a through hardened steel (H11). With this as well the wear behavior, as also the fatigue strength should be improved. However, a proof by a test did not exist.
Comment: Obviously the concerned multispline coupling was always a weak point for wear by micro movements (fretting). It can be supposed that this was promoted from the „fuel lubrication“. The material change supports this assumption. Also a lot comments for the special importance of the alignment of the toothings. Obviously elastic deformations by the torque (result of the test) must be seen as failure causative. In this case, the effectivity of the avoidance of tiny misalignments during assembly must be questioned. Also it is not known, why the wear only occurs at the side of the pump.
Ill. 23.2.2-4 (Lit. 23.2.2 -2): During run up of the aeroengine power before the start of the airplane, the left aeroengine accelerated unaccptable fast. So a fuel shut down got necessary. The nose gear got overloaded during the trial to compensate the pivoting of the airplane, caused by the asymmetric thrust - it broke. The following investigation showed, that a spline toothing of the drive to the fuel control unit was worn. So the connection got out of engagement. Now the control unit recorded an assumed too low rotation speed of the high pressure rotor (Ill. 23.2.2-3) and increased the fuel supply. The wear was traced back to misalignments, due to a rework caused dimensional deviation. Independent from this, the fracture of the nose gear was promoted from a fatigue crack. This crack started at a flaw , caused by too aggressive grinding during overhaul.
Ill. 23.2.2-5: In favourable cases there are
premature hints at failures on multispline
During the failure sequence in multispline couplings by wear, usually develop no larger chips, at least till the final failing. Wear products are fine iron oxides, mixed with remains of lubricant (volume 2, Ill. 6.1-3 and Ill. 6.1-4). They can be identified through an increased clearance and vibrations, caused by a failure betore the total drop out. According to the operating influences and the tribological system (material combinations, Ill. 23.2.2-3) it can come thereby, to different failure appearances (Ill. 23.2.2-2, volume 2, Ill. 6.1-3). A visual finding is naturally depending from the accessibility. This is in many cases given for according targeted maintenance work.
Does a multi spline coupling, lubricated with leakage oil, wear (Ill. 23.2.2-1), at the exit of the coupling red brown traces of a liquid ore past can be identified. These can show features of centrifuging (sketch left).
At dry lubrication, coating or lacking lubrication abrasion as powder develops. The red brown to black powder trickles out of the coupling toothing and disperses powder like in the neighbourhood (sketch right).
The fine wear abrasion let hardly expect in the oil system itself warning deposits at the magnetic plugs (Ill. 22.3.4-7) or filters (Ill. 184.108.40.206-2 and Ill. 220.127.116.11-4). The chance for hints exists from the trend of the abrasion, caused oil contaminations (Ill. 23.2.2-5 and Ill. 22.3.4-9). Thereby new, continuous monitoring systems (Lit. 23.2.2-5) can be beneficial.
Resides the coupling in the fuel, for example in control units and pumps, an identification in time at the wear products is hardly possible.
Ill. 23.2.2-6: The lubrication of multi spline couplings from the drive shafts of accessory devices is in some cases only guaranteed by the leakage oil. Especially at older aeroengine types, where no more experiance is available, attention is demanded. Here „improvement measures” for the avoidance of leakage oil can lead to the surprisingly failing by wear. Then the failure potential is especially high. This is the case, if such a failure occurres not before a longer operation time. This means, that a multitude of aeroenbines can be concerned.
Example 23.2.2-1 (Lit. 23.2.2-9):
The bearing flanks of the multispline toothing between intermediate pressure turbine and
intermediate pressure compressor of all types from a big fan engine, are endangered by wear. The
wear attains up to 0,3 mm. Concerned are about 90 aeroengines. The failures have been
discovered during overhaul. Obviously the OEM evaluates these so, that it can come to the
failing of the shaft connection. In such a case
an overspeed of the turbine rotor must be expected. This can cause the fracture of rotor components from
the turbine with fragment exit.
As measure periodical visual inspections are instructed. The time intervals depend from the determined size of wear. Under 0,025 mm, they must be repeated after 4500 start-shur down cycles, then after 2000. An inspection needs about half an hour.
Obviously an ultrasonic test is also possible. Does it show wear under 0,3 mm (!), the inspection must be repeated after 3000 cycles. Exists more wear, the parts must be exchanged. Additionally a srvice bulletin contains a modification of the lubrication.
Comment: Unfortunately the informations in the documents on hand let several question open. This concerns cause and type of the wear. It can be supposed, that fretting is concerned. The question arises, how it is possible to check sufficient certain the wear at this inside located part, mounted in the aeroengine.
Without more informations it is also inapprehensive, why the ultrasonic inspection should be sufficient, although only an about 10 x higher wear can be identified, compared with the visual inspection. Actually the inspection intervals would have to be significand shorter. Obviously a discovery of the failure in time with a oil monitoring (SOAP) is not possible (Ill. 23.2.2-7).
Example 23.2.2-2 (Lit. 23.2.2-6 and Lit. 23.2.2-10): Concerned is a widely spread
military and civil aeroengine type for helicopters. In several cases it came to the interruption of the
fuel supply. In such a case the consequence is an emergency landing with autorotation.
Cause is wear of the multispline shaft connection from the main drive and auxilary drive to the fuel control unit and the main fuel pump. As well the shaft side as also the toothing of the gear to the pump drive is concerned.
As measure every1250 flight hours a visual and dimensional check is necessary. For this the control unit must be dismounted.
Comment: It can be supposed, that a fuel wetted multispline coupling is concerned. In this case the susceptibility for wear would be explainable with the limited lubrication effect of the fuel (Ill. 23.2.2-3 and Ill. 23.2.2-4). Why seemingly two different coupling connections are affected, is not clear. Possibly vibrations in the drive system play a role.
Ill. 23.2.2-7: The wear mechanism at multi spline toothings produces very fine particles from iron oxide. In many cases, the abrasive does not get into the lubrication oil. Then a detection of the failure at the beginning is only promising with a targeted inspection during a maintenance process (Pand Ill. 23.2.2-5 and example 23.2.2-1). Even if the wear paricles get into the lubrication oil, the chance that this attracts the attention in filters or at magnetic plugs is rather low. More promising in such a case is the trend of oil analysis (Ill. 22.3.4-6 and Ill. 22.3.4-9).
23.2.2-1 NTSB Identification ATL90FA146, microfiche number 45112A, „Accident
Jul-22-90, Aircraft Boeing 737-222“, 1990, page 1.
23.2.2-2 National Transportation Safety Board, Aircraft Accident Report NTSB/AAR-92-93, PB92-910403, „Uncontrolled Collision With Terrain of an Embraer EMB-120, April 5 1991”, page 1-44.
23.2.2-3 National Transportation Safety Board, Safety Recommendation to A-98-67-70, page 1-5.
23.2.2-4 Australia Civil Aviation Safety Authority, Airworthiness Directive AD/JT8D/39 „Fuel Pump Inspection and Modification“, 5/2002, page 1and 2.
23.2.2-5 D.Aslin, „Monitoring Bearing and Gear Failures in Aircraft Gas Turbine Engines”, Zeitschrift „ Sensor Business Digest“, December 2001, www.sensorsmag.com/articles, page 1-7.
23.2.2-6 I.E.Traeger, „Aircraft Gas Turbine Engine Technology, Second Edition”, Verlag : Glencoe/McGraw-Hill 1994, ISBN 0-07-065158-2, page 260.261, 398, 403, 423-435, 442, 500, 531, 549.
23.2.2-7 „The Jet Engine“, Rolls-Royce.plc. 1986, 994, ISBN 0-902121-2-35, Ausgabe 1996, page 67-71.
23.2.2-8 M.J.Kroes, T.W.Wild, „Aircraft Powerplants, Seventh Edition”, Verlag : Glencoe/McGraw-Hill 1990, ISBN 0-02-801874-5, page 304, 313, 454, 468.
23.2.2-9 Federal Aviation Administration (FAA), Airworthiness Directive No. 2002-NE-19-AD; AD 2004-13-11, RIN 2120-AA64, „Trent Series Turbofan Engines“, page 1-5.
23.2.2-10 Federal Aviation Administration (FAA), Airworthiness Directive No.AD/T53/22, 8/2006, „Allied Signal (Lycoming) Turbine Engines - T53 Series, Engine Fuel Pump Spline Failure”, page 1 and 2.