Patent Application
20130022451
The present invention relates to a disk for use in a turbine engine component having a plurality of locking slots in a bearing surface and a system and method for assembling the turbine engine component.
Gas turbine engine have a plurality of compressors arranged in flow series, a plurality of combustion chambers, and a plurality of turbines arranged in flow series. The compressors typically include at least a high pressure compressor and a lower pressure compressor which are respectively driven by a high pressure turbine and a low pressure turbine. The compressors compress the air which has been drawn into the engine and provide the compressed air to the combustion chambers. Exhaust gases from the combustion chambers are received by the turbines which provide useful output power. Each compressor typically has a plurality of stages.
The main components of a typical tangential stage in a high pressure compressor are the disk, the blades, the ladder seals and the locks. The assembly sequence for a typical tangential stage is as follows. First, a ladder seal is assembled to the inner rail of the disk with a first slot of the ladder seal positioned directly over the loading slot in the disk. Second, a first blade is assembled through the ladder seal and through the loading slot in the disk. Then the blade and ladder seal are rotated around the circumference of the disk until the next slot of the ladder seal is positioned directly over the loading slot. In a similar fashion, the next blade is loaded and rotated. Once the blades have been completely loaded and rotated in the ladder seal segment, the lock is assembled through the load slot and rotated to the lock slot position and tightened. The lock prevents the circumferential motion of the blades, which insures that work will be done on the air and that the blades will not come back out through the load slot.
Since locking and loading slots form discontinuities in tangential rotor disks, they have been known to initiate thermal mechanical fatigue (TMF) cracking. The root cause of any TMF cracking is the thermal gradients that exist at certain flight points. One flight point may produce a cold bore and a hot rim, which would put the rim into compression. Another flight point may produce a hot bore and a cold rim which would put the rim into tension. This cyclic loading fatigues the disk. The locking and loading slots may make this condition worse by introducing stress concentrations due to the discontinuities.
The present disclosure illustrates a system for assembling a turbine engine component which achieves a significant improvement in TMF life.
In accordance with the instant disclosure, there is provided a disk which broadly comprises a groove; said groove having a bearing surface and an upper wall; and at least one locking slot being positioned at an intersection of said bearing surface and said upper wall.
Further, in accordance with the present disclosure, there is provided a system for assembling a turbine engine component which broadly comprises a disk having a slot, said slot having a bearing surface, said bearing surface being provided with at least one locking surface for cooperating with a lock; said locking surface having a shape; and at least one lock having a shape which matches and mates with said shape of said locking surface.
Still further, in accordance with the present disclosure, there is provided a method for assembling a turbine engine component, which method broadly comprises providing disk having a groove, said groove having a bearing surface and an upper wall, at least one locking slot being positioned at an intersection of said bearing surface and said upper wall, and each said locking slot having a shaped surface; inserting a first blade into said groove at an angle with respect a final position; rotating said blade into said final position; inserting a lock into said groove; and rotating said lock until said lock engages said at least one locking slot.
Other details of the bearing surface combined load-lock slots for tangential rotors are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
Referring now to
In accordance with the present disclosure, a plurality of slots 24 are cut into the bearing surface 16 where the bearing surface 16 intersects the upper wall 18. The slots 24 are spaced at discrete locations along the length of the groove 12. By positioning the slots 24 in this area, associated stress concentrations are moved into a lower stress, lower temperature area, thereby increasing TMF life.
A plurality of locks 30 are provided to engage the slots 24. The locks 30 are spaced out along the length of the groove 12. Referring now to
To assemble the turbine engine component to be used in the turbine engine, a first blade 22 is inserted into the tangential groove 12 at 90 degrees with respect to the blade's final position at load/lock slot location (see
After the first blade 22 has been installed and rotated into position, a lock 30 may be introduced into the groove 12. The lock 30 is rotated into position so that the end portions 64 each engage one of the slots 24.
After the lock is installed, a second blade 22 is introduced into the groove 12 and rotated into position. As shown in
One of the principal gains from the system disclosed herein is that TMF life is extended due to the movement of the slots into a lower stress and/or lower temperature region of the disk.
There has been provided herein a bearing surface combined load/lock slot for tangential rotors. While the specific embodiments have been described herein, other unforeseen alternatives, modifications, and variations may become apparent to those skilled in the art. It is intended to embrace those alternatives, modifications, and variations as fall within the broad scope of the appended claims.
