A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first di
A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.
대표청구항▼
1. A duct assembly, comprising: a casing body that extends between a flange and a wall;a first discrete cooling passage formed in said casing body;a second discrete cooling passage circumferentially spaced from said first discrete cooling passage, wherein at least one of said first discrete cooling
1. A duct assembly, comprising: a casing body that extends between a flange and a wall;a first discrete cooling passage formed in said casing body;a second discrete cooling passage circumferentially spaced from said first discrete cooling passage, wherein at least one of said first discrete cooling passage and said second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of said first and second discrete cooling passages;a case that interfaces with said flange at a joint between said case and said casing body such that said at least one of said first discrete cooling passage and said second discrete cooling passage extends from said joint, said joint being a male/female connection with one of said flange and an end of said case defining a female portion of said connection and another one of said flange and said end of said case defining a male portion of said connection; andat least one view port that extends through said wall, said at least one view port providing a line of sight to said joint. 2. The duct assembly as recited in claim 1, wherein said duct assembly is a tangential onboard injection (TOBI) assembly. 3. The duct assembly as recited in claim 1, comprising a first component that is conditioned by said cooling fluid. 4. The duct assembly as recited in claim 3, comprising a second component that is conditioned by a second cooling fluid communicated along an outer surface of said casing body, said second component different from said first component. 5. The duct assembly as recited in claim 1, comprising a plug removably insertable into said at least one view port. 6. The duct assembly as recited in claim 5, comprising a retainer received within a slot of said at least one view port for retaining said plug within a bore of said at least one view port. 7. The duct assembly as recited in claim 1, comprising a plurality of discrete cooling passages cast in said casing body and configured to channel said cooling fluid to condition hardware positioned at least partially outboard from said casing body. 8. The duct assembly as recited in claim 1, wherein the at least one view port is a plurality of view ports annularly spaced along said wall, each of said plurality of view ports providing a line of sight to said flange. 9. The duct assembly as recited in claim 1, wherein said first discrete cooling passage includes said axial portion and said tangential portion, and said axial portion extends from said joint. 10. The duct assembly as recited in claim 9, wherein said end of said case is insertable into said flange such that an end of said flange abuts a protrusion of said case. 11. A gas turbine engine, comprising: a case having at least one opening that communicates a cooling fluid;a duct assembly including a flange connected to said case to define a joint;said duct assembly having a casing body, at least one discrete cooling passage formed in said casing body that extends between said flange and a wall, and at least one view port defined in said wall that is configured to provide visualization of at least a portion of said joint;wherein said joint is a male/female connection including a male portion insertable into a female portion such that said at least one discrete cooling passage extends from said joint; andwherein said at least one view port provides a line of sight to said joint. 12. The gas turbine engine as recited in claim 11, wherein said at least one discrete cooling passage is configured to communicate said cooling fluid between a first location and a second location of the gas turbine engine. 13. The gas turbine engine as recited in claim 12, comprising a second cooling fluid communicated across at least one airfoil of said duct assembly to a third location of the gas turbine engine. 14. The gas turbine engine as recited in claim 13, wherein said at least one discrete cooling passage extends from said joint, and said at least one discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated from said at least one opening to said at least one discrete cooling passage. 15. The gas turbine engine as recited in claim 14, wherein said case is a diffuser case of a combustor section that extends radially inwardly from a combustor shell, and said wall is positioned adjacent to a rotor assembly of a turbine section. 16. The gas turbine engine as recited in claim 15, wherein said at least one discrete cooling passage is a plurality of discrete cooling passages circumferentially spaced apart and axially extending through said casing body. 17. The gas turbine engine as recited in claim 11, wherein said duct assembly includes a plurality of discrete cooling passages circumferentially spaced apart and axially extending through said casing body. 18. The gas turbine engine as recited in claim 11, wherein said duct assembly includes a plurality of view ports that provide a line of sight to said joint.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (7)
Mize Christopher D. (Palm Beach Gardens FL) Pirsig William W. (Manchester CT) Vercellone Peter T. (North Haven CT), Anti-contamination thrust balancing system for gas turbine engines.
Ottaviano, Marcus Joseph; Parks, Robert John; Noon, John Lawrence; D'Andrea, Mark Michael; Regan, Thomas Michael, Turbine cooling air from a centrifugal compressor.
Soechting Friedrich O. (Tequesta FL) Plank William L. (Tequesta FL) Hall Kenneth B. (Klingnau CHX), Turbine vane assembly with multiple passage cooled vanes.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.