|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3936 ; 60/760|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 8 인용 특허 : 0|
Difficulties in cooling the shrouds (32, 34) and the nozzle (38) of an air breathing gas turbine are minimized or eliminated through the use of a generally toroidal, annular combustor (44) having an outlet (48) and combustion air inlets (90A, 90B) and otherwise being imperforate or free of any means for the admission of cooling air to the interior of the combustor (44).
A gas turbine engine comprising: a rotary compressor; a turbine wheel coupled to said rotary compressor; an annular nozzle for directing gases of combustion at said turbine wheel to drive the same; an annular plenum in fluid communication with said compressor to receive compressed air therefrom; and a toroidal combustor within said plenum and having an annular outlet connected to said nozzle, said combustor further having an air inlet means connected to said plenum for allowing entry of air necessary to support combustion and defined by tubular elements ...