Abstract:
An assembly for connecting a coverplate and a rotor includes a first rotor for use in a rotating engine; a first cover mounted to the first rotor, wherein the rotor and the cover create a space there between, the space for having cooling air therein; and a lock assembly for preventing the cover from rotating circumferentially or moving axially away from the rotor if mounted to the to the rotor wherein the cover is sealed against the rotor.

Description:
TECHNICAL FIELD 
     This invention relates to disks for gas turbine engines and particularly to coverplates that fit adjacent the recesses in the disks to provide a cooling path there between. 
     BACKGROUND OF THE INVENTION 
     Early coverplates were used as windage covers disposed upon rotating gas turbine engine disks. More modern coverplates are also used to attain a cooling of the disk. An axial extension of the cover may extend into a broach area of a turbine disk (or rotor) radially outside the disk rim and radially supported by the blade. The coverplate is spaced radially from the disk to provide a dead ended annular space. Cooler air migrates to this space and insulates the disk rim from the engine&#39;s extremely hot working medium that is acting on the turbine blades. Tests have shown that this feature reduces the disk rim temperature by over 100 degree F. which increases the disk low cycle fatigue life and allows the use of less expensive material from which the disk is fabricated. 
     SUMMARY 
     According to an embodiment shown herein, an assembly for connecting a part to a rotor includes: a first rotor for use in a rotating engine; a part mounted to the first rotor; and, a lock preventing the first part from rotating circumferentially or moving axially away from the rotor if mounted to the rotor wherein the lock performs another function other than preventing the part from rotating circumferentially or moving axially away from the rotor. 
     According to any previous embodiment described herein, the assembly lock includes a first tab mounted to the rotor, a second tab mounted to the cover, wherein the second tab is axially aligned with the first tab; and a tooth preventing the first tab and the second tab from being unaligned with each other. 
     According to any previous embodiment described herein, the first tab is axially aft the second tab. 
     According to any previous embodiment described herein, the second tab is axially aft the first tab. 
     According to any previous embodiment described herein, the first tooth is attached to a sleeve. 
     According to any previous embodiment described herein, the sleeve encircles a hub of the first rotor. 
     According to any previous embodiment described herein, the tooth attaches to a second rotor. 
     According to any previous embodiment described herein, the first tab is axially aft of the second tab. 
     According to any previous embodiment described herein, the cover has a reinforced area adjacent the tab, the reinforced area for minimizing torque effects on the cover. 
     According to any previous embodiment described herein, the first cover is urged against the first rotor if the first tab is disposed behind the second tab. 
     According to any previous embodiment described herein, the first cover has a gap between adjacent teeth thereof, the gap angling axially forward and radially inwardly from an aft surface of the cover. 
     According to a further embodiment disclosed herein, an assembly includes a first rotor for use in a rotating gas turbine engine; a first cover mounted to the first rotor, wherein the rotor and the cover create a space there between, the space for having cooling air therein; and a lock assembly for preventing the cover from rotating circumferentially or moving axially away from the rotor if mounted to the to the first rotor wherein the cover is sealed against the rotor wherein the lock assembly includes; a first tab mounted to the rotor, a second tab is mounted to the cover, wherein the second tab is axially aligned with the first tab; and a tooth preventing the first tab and the second tab from being unaligned with each other. 
     According to any previous embodiment described herein, the first tooth is attached to a sleeve. 
     According to any previous embodiment described herein, the tooth attaches to a second rotor. 
     According to any previous embodiment described herein, the first cover is urged against the rotor if the first tab is disposed behind the second tab. 
     According to a still further embodiment disclosed herein, a coverplate for use with a rotor includes a plate like body, a plurality of teeth extending radially inwardly from a central opening in the body, and a thickened area axially and radially adjacent the teeth. 
     According to any previous embodiment described herein, the first cover has a gap between adjacent teeth thereof, the gap angling axially forward and radially inwardly from an aft surface of the cover. 
     According to still further embodiment described herein, disclosed herein a method of assembling a coverplate and a rotor includes the following steps: providing a first rotor for use in a rotating gas turbine engine, the rotor having a first plurality of tabs mounted thereto the first tabs having a first gap disposed between each adjacent first tab; providing a first cover having a plurality of second tabs mounted thereto the second tabs having a second gap disposed between each adjacent second tab; maneuvering the first tabs through the second gaps or the second tabs through the first gaps, and rotating the cover relative to the hug to align the first tabs and the second tabs axially. 
     According to any previous embodiment described herein, the method further includes filling the first gap or the second gap such that the first tabs may not rotate circumferentially relative to the second tabs. 
     According to any previous embodiment described herein, the method further includes filling the first gap or the second gap such that the first tabs may not rotate circumferentially relative to the second tabs nor may the cover move axially away from the rotor wherein the rotor and the cover creating a space there between, the space for having cooling air therein. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows. 
         FIG. 1  shows a gas turbine engine, including non-limiting embodiment of the invention. 
         FIG. 2  is a side view of a turbine section of the engine of  FIG. 1 . 
         FIG. 3  is a perspective, aft view of a rotor along the line  3 - 3  of  FIG. 2 . 
         FIG. 4A  is a perspective view, taken along the lines  4 - 4  of  FIG. 2  of an aft coverplate for use with forward rotor. 
         FIG. 4B  is a side view of the aft coverplate taken along the lines  4 B- 4 B of  FIG. 4A . 
         FIG. 5  is a depiction of an assembly of the forward rotor and the aft coverplate associated with the forward rotor of  FIG. 2 . 
         FIG. 6A  is a side view taken along lines  6 - 6  of  FIG. 6B . 
         FIG. 6B  is a perspective view of the coverplate of  FIG. 6A . 
         FIG. 7A , is a perspective view taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in  FIG. 2 . 
         FIG. 7B , is a perspective side views taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in  FIG. 2 . 
         FIG. 7B , is a perspective side views taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in  FIG. 2 . 
         FIG. 7C , is a perspective view, partially in section, taken of a combination of a sleeve, an aft coverplate and the aft rotor taken along the lines  7 C- 7 C of  FIG. 7A . 
     
    
    
     DETAILED DESCRIPTION 
     Referring to  FIG. 1 , a gas turbine engine  10  includes a fan section  15 , a compressor section  20 , a combustor  25  and a turbine section  30 . The example compressor section  20  includes a low pressure compressor section  35  and a high pressure compressor section  40 . The turbine section  30  includes a high pressure turbine  45  and a low pressure turbine  50 . The high pressure compressor section  40  and the high pressure turbine  45  are supported by a high spool  55 . The low pressure compressor section  35  and low pressure turbine  50  are supported on a low spool  60 . Spools  55  and  60  and their attached components rotate about a main axis A. Air drawn in through the compressor section  20  is compressed and fed into the combustor  25 . In the combustor  25 , the compressed air is mixed with fuel and ignited to generate a high speed gas stream. This gas stream is drives the turbine section  30 . 
     Referring now to  FIG. 2 , a depiction of a turbine assembly  45  is shown. One of ordinary skill in the art will recognize that the teachings of this invention may be used for either the high pressure turbine assembly  40  or the low pressure turbine assembly  45 . Moreover, one of ordinary skill will recognize that the teachings herein can be used wherever rotors or blades need to be cooled and may include other parts of the engine like the high pressure compressor section  40 , more turbine stages or other types of engines besides the gas turbine engine  10  shown herein. 
     Referring again to  FIG. 2 , a rotor assembly includes a forward rotor  65 , an aft rotor  70 . A forward rotor forward coverplate  75  defines a space  77  between the forward rotor forward coverplate  75  and the forward rotor  65 ; a forward rotor aft coverplate  80  defines a space  83  between the forward rotor aft coverplate  80  and the forward rotor  65 ; and, an aft rotor forward coverplate  85  defines a space  87  between the aft rotor forward coverplate  85  and the aft rotor  70 . An aft rotor aft coverplate  90  defines a space  91  between the aft rotor aft coverplate  90  and the aft rotor  70 . The aft rotor  70  has axially extending teeth  93  that extend forward therefrom. A sleeve  94  attaches to an aft side  96  of the aft rotor  70  as will be discussed herein. 
     Referring now to  FIG. 3 , a perspective aft view of a forward rotor  65  is shown. The forward rotor  65  has a body  95  that has a plurality of radially extending teeth  100  (shown generically) that holds blades (not shown) as is known in the art. The forward rotor  65  has an aft hub  105  that has a plurality of aft tabs  110 . The aft tabs  110  each have a forward surface  113  for engaging the aft rotor aft coverplate  90  as will be discussed herein. An area  120  between the aft tabs  110  and the body  95  receives the teeth  93  of the aft rotor  70 , forward tabs  110  and the aft coverplate  80  as will be discussed herein. 
     Referring to  FIG. 4A and 4B , a side view and a perspective view of the forward rotor  65  aft coverplate  80  is shown. Coverplate  80  has a body  163 , a forward surface  165 , cogs  185  and central opening  187 . Passageways  190  are formed between adjacent cogs which extend radially inwardly. Each passageway  190  has an angled surface  191  that extends radially outwardly and axially aft from the aft surface  195  to the forward surface  165 . The cogs  185  have a flat surface  200  that pushes against the forward surface  113  of the aft tabs  110  on the forward rotor  65 . The coverplate  80  has an area  205  axially forward and radially inward of each cog  85 , which is a thickened (or reinforced), to withstand any torque placed on the coverplate. 
     Referring now to  FIG. 5 , an assembly  206  of the aft coverplate  80 , the forward rotor  65 , and the aft rotor  70  is shown. The aft coverplate  80  is inserted through slots  120  between aft tabs  110 . The coverplate  80  is then rotated circumferentially about the aft hub  105  so that the cogs  185  are disposed in register and axially aligned with forward surface  113  and the flat surface  200  is contacting the forward surface of aft tabs  110 . Axially extending teeth  193  from the aft rotor  70  are then pushed into gaps  113  to lock the coverplate  80  axially forward the aft tabs  110  (see Also  FIG. 2 ). The aft coverplate  80  may not now move circumferentially because of the interaction of the teeth  193  extending between the cogs  185  nor may it move axially because the disposition of the cogs  185  axially forward and in register with forward surface  113  of aft tabs  110 . The teeth  193  act as a lock to lock the cogs  185  axially forward and in register with forward surface  113  of aft tabs  110 . The aft coverplate  80  (like all coverplates described herein) is flexible such that as the coverplates are installed, they flex to allow the sealing surfaces  180  to seal against the forward rotor  65 . 
     Referring now to  FIGS. 6A and 6B , a side and a perspective view of the aft rotor  70  aft cover  90  is shown. The aft rotor  70  aft cover  90  has a body  210 , a forward side  215 , an aft side  220 . A plurality of bayonet tabs  240  extends from a radially inner portion  242  and an axially aft portion  243  of the aft rotor aft cover  90 . One of ordinary skill in the art will notice that the forward rotor  65  forward coverplate  75  is constructed and interacts with the forward rotor  65  in the same manner as the aft rotor aft coverplate  90  does with the aft rotor  70  though tabs  266  in the forward coverplate  75  are disposed behind tabs  267  in the forward rotor  65 . 
     Referring now to  FIGS. 7A-7C , the aft rotor  70  is shown in conjunction with the aft rotor aft coverplate  90  and sleeve  94 . Similar in construction to the forward hub  125  of the forward rotor  65 , the aft rotor  65  has an aft hub  246 . A plurality of aft tabs  241  extend radially outwardly from the aft hub  246 . The aft tabs have a forward surface  243  for engaging the aft rotor aft coverplate  90  as will be discussed herein. 
     The sleeve  94  has a plurality of sprockets  245  that extend axially forward from end  250  of the sleeve  94 . Gaps  246  extend between the sprockets  245 . 
     Referring now to  FIGS. 7B and 7C , an assembly  260  that includes the sleeve  94 , the aft rotor  70  and the aft rotor aft coverplate  90  is shown. The bayonet tabs  240  of the aft coverplate  90  are inserted from aft through gaps  247 . The coverplate  90  is then rotated circumferentially about the aft hub  246  so that the bayonet tabs  240  of the aft rotor  70  are disposed behind, axially aligned with each other and in contact with the forward surface  243  of the aft tabs  241  extending from the aft hub  246 . Because, the bayonet tabs  240  are no longer in the gaps  247 , the sprockets  245  are then inserted in the gaps  247  to lock the bayonet tabs  240  forward of the aft tabs  241 . The aft coverplate  90  may not now move circumferentially nor may it move axially because the bayonet tabs  240  of the aft rotor  70  are disposed axially forward and in contact with the forward surface  243  of the aft tabs  241 . The sprockets  245  act as a lock to lock the bayonet tabs  240  axially forward and in register with forward surface  243  of the aft tabs  241 . 
     By using the assemblies  206 ,  260 , a part such as a coverplate  80  or  90  may be attached to a rotor  65 ,  70  with a single assembly that performs another function. For instance assembly  206 , which includes the aft coverplate  80 , the forward rotor  65 , and the aft rotor  70 , acts to drive torque. Similarly, the assembly  260 , which includes the sleeve  94 , the aft rotor  70  and the aft rotor aft coverplate  90 , acts as a heat shield and a spacer. No parts are added with the sole function of locking the rotor and the part together. Each portion of the assembly performs more than one function in the engine  100  than locking the part such as a coverplate  80  or  90  to the rotor  65  or  70 . 
     The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.