Fitting for mid-turbine frame of gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/12
F01D-025/28
F02C-007/18
F01D-025/14
출원번호
US-0696615
(2015-04-27)
등록번호
US-9988943
(2018-06-05)
발명자
/ 주소
Chasse, Jr., James P.
Snyder, Ryan K.
Ackermann, William K.
Pisacreta, Pellegrino J.
Brooks, Judith F.
Ernst, Stephanie
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet inclu
A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.
대표청구항▼
1. A fitting, comprising: a main body portion having a first axial end and a second axial end opposite the first axial end;an inlet provided at the first axial end;an outlet adjacent the second axial end, wherein the outlet includes a plurality of circumferentially spaced-apart slots formed through
1. A fitting, comprising: a main body portion having a first axial end and a second axial end opposite the first axial end;an inlet provided at the first axial end;an outlet adjacent the second axial end, wherein the outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and wherein each slot has an area within a range of 0.52 and 0.59 square inches; anda support flange, wherein the support flange is generally triangular in shape and has three corners, and wherein the support flange includes an opening for receiving a fastening element at each of the three corners. 2. The fitting as recited in claim 1, further comprising a deflector plate provided at the second axial end of the main body portion, the deflector plate oriented substantially perpendicular to a central fitting axis. 3. The fitting as recited in claim 1, wherein the fitting consists of three slots, and wherein the slots are equally circumferentially spaced-apart from one another relative to a central fitting axis. 4. The fitting as recited in claim 1, wherein each of the slots has a length dimension parallel to a central fitting axis, and wherein the length dimension is within a range of 0.74 and 0.76 inches. 5. The fitting as recited in claim 4, wherein each of the slots has a width dimension perpendicular to a central fitting axis, and wherein the width dimension is within a range of 0.73 and 0.75 inches. 6. The fitting as recited in claim 1, wherein each of the slots has a length dimension parallel to a central fitting axis, and wherein a ratio of the length dimension to an overall length of the fitting within a range of 0.262 to 1 and 0.271 to 1. 7. The fitting as recited in claim 1, wherein the main body portion includes threads for mating with threads of a conduit. 8. The fitting as recited in claim 1, wherein the fitting is integrally formed of a single piece of material. 9. The fitting as recited in claim 8, wherein the material is a stainless steel. 10. The fitting as recited in claim 1, wherein the main body portion is substantially cylindrically shaped. 11. A gas turbine engine, comprising: a gas path wall providing a radially outer boundary of a core airflow path;an external housing radially spaced-apart from the gas path wall;a source of cooling fluid; anda fitting fluidly coupled to the source of cooling fluid and configured to direct cooling fluid from the source to a location radially between the gas path wall and the external housing, the fitting including an inlet at a first axial end and an outlet adjacent a second axial end, wherein the outlet is provided by a plurality of circumferentially spaced-apart slots, and wherein each slot has an area within a range of 0.52 and 0.59 square inches, wherein the fitting consists of three slots, and wherein the three slots are equally circumferentially spaced-apart from one another relative to a central fitting axis. 12. The gas turbine engine as recited in claim 11, wherein the external housing is a core nacelle housing. 13. The gas turbine engine as recited in claim 12, wherein the source of cooling fluid is a high pressure compressor. 14. The gas turbine engine as recited in claim 11, wherein the fitting includes a deflector plate at the second axial end, wherein the deflector plate is arranged such that fluid enters the inlet flowing in a direction substantially parallel to a central fitting axis, and is expelled from the outlet in a direction perpendicular to the central fitting axis. 15. The gas turbine as recited in claim 11, wherein each of the slots has a length dimension parallel to a central fitting axis, and wherein the length dimension is within a range of 0.74 and 0.76 inches. 16. The gas turbine as recited in claim 15, wherein each of the slots has a width dimension perpendicular to a central fitting axis, and wherein the width dimension is within a range of 0.73 and 0.75 inches. 17. The gas turbine engine as recited in claim 11, wherein each of the slots has a length dimension parallel to a central fitting axis, and wherein a ratio of the length dimension to an overall length of the fitting is within a range of 0.262 to 1 and 0.271 to 1. 18. A gas turbine engine, comprising: a gas path wall providing a radially outer boundary of a core airflow path;an external housing radially spaced-apart from the gas path wall;a source of cooling fluid; anda fitting fluidly coupled to the source of cooling fluid and configured to direct cooling fluid from the source to a location radially between the gas path wall and the external housing, the fitting including an inlet at a first axial end and an outlet adjacent a second axial end, wherein the outlet is provided by a plurality of circumferentially spaced-apart slots, and wherein each slot has an area within a range of 0.52 and 0.59 square inches;wherein the external housing is a core nacelle housing;wherein the source of cooling fluid is a high pressure compressor;wherein the fitting is disposed in a mid-turbine frame of the engine.
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