|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||415/175 ; 415/115 ; 415/177|
|§371/§102 date||19930622 (19930622)|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 28 인용 특허 : 0|
A gas turbine engine includes a casing cooling system which operates in one of two conditions, the first being operational at engine cruise, where all of the cooling air is initially directed onto a specific region of the casing; under full power conditions, some of the cooling air is directed onto the specific casing region and the reminder directed onto the reminder of the casing; the cooling system operates to optimize turbine blade/casing radial clearances.
A gas turbine engine turbine comprising a casing enclosing a plurality of annular arrays of rotor aerofoil blades, said blades being arranged in radially spaced apart relationship with said casing, means being provided to direct cooling air onto the outer surface of said casing to provide cooling thereof, control means being provided to control the distribution of cooling air so directed onto said casing between two circumferential axially adjacent regions of said casing, one of said region being axially forward and the other rearward of said forward reg...