Abstract:
A connecting arrangement is disclosed for connecting first and second articles, such as casing sections ( 22, 24 ) to each other. The connecting arrangement comprises a connector ( 28 ) comprising an outwardly extending portion, which may be a first flange ( 34 ). The outwardly extending portion is securable to an outwardly extending member, which may be a second flange ( 36 ). A securing portion ( 30 ) removably secures the connector ( 28 ) to the first article.

Description:
FIELD OF THE INVENTION 
   This invention relates to connecting arrangements. More particularly, but not exclusively, the invention relates to connecting arrangements to connect together casings for engines, for example gas turbine engines. 
   BACKGROUND OF THE INVENTION 
   The casing of a gas turbine engine, and other pieces of equipment can be formed in several sections which are connected together by means of flanges extending around the casing or the piece of equipment. Often, these flanges can inhibit transportation or restrict machining operations. 
   SUMMARY OF THE INVENTION 
   According to one aspect of this invention, there is provided a connecting arrangement to connect first and second articles to each other, comprising a connector comprising outwardly extending portion securable to an outwardly extending member on the second article, and a securing portion for removably securing the connector to the first article. 
   The outwardly extending portion on the connector is conveniently a radially outwardly extending portion. 
   The first article preferably comprises a cylindrical structure. The first article may comprise a casing or a section of a casing. The casing or section thereof may be an engine casing or section thereof, such as a casing or section thereof for a component of a gas turbine engine. 
   The second article preferably comprises a cylindrical structure. The second article may comprise a casing or a section of a casing, which may be an engine casing or section thereof, such as a casing for a component of a gas turbine engine. 
   The connector may be configured to extend at least partially around the first article. Preferably, the connector is configured to extend substantially half way round the first article. 
   The connecting arrangement may comprise a further connector which preferably can extend at least partially around the first article. Conveniently, the further connector can extend substantially half way round the first article, whereby each of the connectors may comprise an outwardly extending portion which may be securable to the outwardly extending member on the second article. The outwardly extending portion on the further connector is a radially outwardly extending portion. 
   Where the first article is generally circular in profile, the, connector may extend at least over an arc of a circle. In the preferred embodiment, the connector may extend over substantially a semi-circle. The further connector may also extend over an arc of a circle, preferably over a semi-circle. 
   Preferably, the securing portion comprises a first cooperating formation on the connector. The connecting arrangement may comprise a second cooperating formation on the first article. The second cooperating formation may be integral with the first article. The first and second cooperating formations may cooperatively engage each other to attach the, or each, connector to the first article. 
   The first and second cooperating formations may respectively comprise corresponding first and second hook formations. 
   Preferably, the first cooperating formation extends along the outwardly extending portion. The second cooperating formation preferably extends around the first article. Preferably, the, outwardly extending portion of the connector may be secured to the outwardly extending member on the second article by fastening means. The fastening means may comprise suitable threaded members, for example bolts, or nuts and bolts. Preferably, the outwardly extending portion comprises a flange. The outwardly extending member on the second article may also comprise a flange. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
     An embodiment of the invention will now be described by way of example only, with reference to the accompanying drawings, in which: 
       FIG. 1  shows a sectional side view of the upper half of a gas turbine engine; 
       FIG. 2  is a cross-sectional side view of two sections of a casing used in the engine shown in  FIG. 1 , and incorporating a connecting arrangement; and, 
       FIG. 3  is a perspective view of the two sections of the casing and the connecting arrangement shown in  FIG. 2 . 
   

   DETAILED DESCRIPTION OF THE INVENTION 
   Referring to  FIG. 1 , a gas turbine engine is generally indicated at  10  and comprises, in axial flow series, an air intake  11 , a propulsive fan  12 , an intermediate pressure compressor  13 , a high pressure compressor  14 , a combustor  15 , a turbine arrangement comprising a high pressure turbine  16 , an intermediate pressure turbine  17  and a low pressure turbine  18 , and an exhaust nozzle  19 . 
   The gas turbine engine  10  operates in a conventional manner so that air entering the intake  11  is accelerated by the fan  12  which produce two air flows: a first air flow into the intermediate pressure compressor  13  and a second air flow which provides propulsive thrust. The intermediate pressure compressor compresses the air flow directed into it before delivering that air to the high pressure compressor  14  where further compression takes place. 
   The compressed air exhausted from the high pressure compressor  14  is directed into the combustor  15  where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines  16 ,  17  and  18  before being exhausted through the nozzle  19  to provide additional propulsive thrust. The high, intermediate and low pressure turbines  16 ,  17  and  18  respectively drive the high and intermediate pressure compressors  14  and  13  and the fan  12  by suitable interconnecting shafts. 
   Some components of the gas turbine engine  10 , for example turbines and compressors, are contained within a casing. 
   Referring to  FIGS. 2 and 3  of the drawings, there is shown a casing  20  for a component of the gas turbine engine  10 . The casing  20  comprises first and second sections  22 ,  24 . The first section  22  is attached to the second section by a removable connecting member in the form of a removable clamping ring  26 . The clamping ring  26  comprises two semi-circular ring members  28 ,  29  is shown. Each ring member includes a semi-circular first hook formation  30 . The first section  22  also includes a corresponding annular second hook formation  32  which cooperatively engages each of the semi-circular first hook formations  30  on the respective members. The first hook formations  30  are each provided on a respective one of the ring members  28  and the second hook formation  32  extends around the circumference of the first section  22  of the casing,  22  as shown. 
   Each clamping ring member  28 ,  29  also includes a radially outwardly extending portion in the form of a first radially outwardly extending flange  34 . 
   A corresponding radially outwardly extending second flange  36  is provided integrally on the second casing section  24 , whereby when the first hook formation  30  on each of the clamping ring members  28  cooperatively engages the second hook formation  32  on the first casing section  22 , the first and second flanges  34 ,  36  engage each other at their respective axially facing surfaces  38 ,  40 . 
   The first and second flanges  34 ,  36  define a plurality of corresponding apertures  37 ,  39 . The apertures  37 ,  39  in the first and second flanges  34 ,  36  can be aligned with each other so that shanks of bolts  42  can be inserted therethrough and nuts  44  tightened thereon. The clamping ring  26  is secured to the second flange  36  and thereby to the second casing section  24 . Also the clamping ring  26  is secured to the first casing section  22  via the co-operative engagement of the first and second hook formations  30 ,  32 . Thus the first casing section  12  and the second casing section  14  are connected together. 
   There is thus described a connection arrangement which enables two sections of an engine casing, for example an engine casing of a gas turbine engine to be connected together. The embodiment described above has the advantage that it allows the first casing section to be transported through restricted openings or machined without any flange obstructing transportation or machining. 
   Various modifications can be made without departing from the scope of the invention. 
   Whilst endeavouring in the foregoing specification to draw attention to those features of the invention believed to be of particular importance it should be understood that the Applicant claims protection in respect of any patentable feature or combination of features hereinbefore referred to and/or shown in the drawings whether or not particular emphasis has been placed thereon.