[특허]Gas turbine engine with high speed low pressure turbine section

Gas turbine engine with high speed low pressure turbine section 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-003/06 F02C-007/36 F02K-003/02 F02K-003/06 F02C-003/04 F02K-003/04 F02K-003/072
출원번호	US-0568167 (2014-12-12)
등록번호	US-9845726 (2017-12-19)
발명자 / 주소	Suciu, Gabriel L. Schwarz, Frederick M. Ackermann, William K. Kupratis, Daniel Bernard
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, PC
인용정보	피인용 횟수 : 0 인용 특허 : 31

초록 ▼

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between abo

대표청구항 ▼

1. A gas turbine engine comprising: a fan;a compressor section in fluid communication with the fan, the compressor section including a first compressor section and a second compressor section;a combustion section in fluid communication with the compressor section;a turbine section in fluid communication with the combustion section;wherein the turbine section includes a first turbine section and a second turbine section;wherein said first turbine section has a first exit area at a first exit point and is configured to rotate at or below a first speed;wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at or below a second speed, which is higher than the first speed, said first and second speeds being redline speeds;wherein a first performance quantity is defined as the product of the first speed squared and the first area;wherein a second performance quantity is defined as the product of the second speed squared and the second area;wherein a ratio of the first performance quantity to the second performance quantity is between 0.5 and 1.5; andwherein a gear reduction is included between said fan and a low spool driven by the first turbine section such that the fan rotates at a lower speed than the first turbine section. 2. The gas turbine engine as set forth in claim 1, wherein said ratio is above or equal to 0.8. 3. The gas turbine engine as set forth in claim 2, wherein said ratio is above or equal to 1.0. 4. The gas turbine engine as set forth in claim 1, wherein said fan has 26 or fewer blades. 5. The gas turbine engine as set forth in claim 1, wherein said first turbine section has at least three stages. 6. The gas turbine engine as set forth in claim 5, wherein said first turbine section has up to six stages. 7. The gas turbine engine as set forth in claim 1, wherein there is a third turbine section driving the fan, the second and third turbine rotors each driving a compressor rotor of the compressor section. 8. The gas turbine engine as set forth in claim 1, wherein the gear reduction is positioned intermediate the fan and a compressor rotor driven by the first turbine section. 9. The engine as set forth in claim 1, wherein the gear reduction is positioned intermediate the first turbine section and a compressor rotor driven by the first turbine section. 10. The gas turbine engine as set forth in claim 1, wherein the first turbine section and the first compressor section rotate in a first direction, and wherein the second turbine section and the second compressor section rotate in a second direction, opposed to said first direction. 11. The gas turbine engine as set forth in claim 10, wherein said gear reduction causes said fan to rotate in the second direction. 12. The gas turbine engine as set forth in claim 10, wherein said gear reduction causes said fan to rotate in the first direction. 13. The gas turbine engine as set forth in claim 12, wherein said gear reduction is a planetary gear reduction. 14. A turbine section of a gas turbine engine comprising: a first turbine section;a second turbine section;wherein said first turbine section has a first exit area at a first exit point and is configured to rotate at or below a first speed, said first turbine section having at least 3 stages;wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at or below a second speed, which is faster than the first speed, said first and second speeds being redline speeds, said second turbine section having 2 or fewer stages;wherein a first performance quantity is defined as the product of the first speed squared and the first area;wherein a second performance quantity is defined as the product of the second speed squared and the second area; andwherein a ratio of the first performance quantity to the second performance quantity is between 0.5 and 1.5. 15. The turbine section as set forth in claim 14, wherein said first and second turbine sections are designed to rotate in opposed directions relative to each other. 16. The turbine section as set forth in claim 14, wherein said ratio of the performance quantities is above or equal to 0.8. 17. The turbine section as set forth in claim 16, wherein said ratio is above or equal to 1.0. 18. The turbine section as set forth in claim 14, wherein said first turbine section has up to six stages.

이 특허에 인용된 특허 (31)

Grieb Hubert (Germering DEX), Combined multi-speed jet engine for the drive of airplanes and space vehicles.
상세보기
Eveker Kevin M. ; Gysling Daniel L. ; Nett Carl N. ; Wang Hua O., Compressor stall and surge control using airflow asymmetry measurement.
상세보기
Taylor,Mark D.; Harvey,Neil W., Counter-rotating turbine engine including a gearbox.
상세보기
Sheridan William G. (Southington CT) Pagluica Gino J. (Manchester CT), Coupling system for a planetary gear train.
상세보기
Hermann Klingels DE, Driving mechanism with counter-rotating rotors.
상세보기
Sheridan, William G., Epicyclic gear train for turbo fan engine.
상세보기
Duong, Loc; McCune, Michael E.; Dobek, Jr., Louis J., Epicyclic gear train integral sun gear coupling design.
상세보기
Stickler David B. ; Kerrebrock Jack L., Evaporatively cooled rotor for a gas turbine engine.
상세보기
Baran, Kenneth C., Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system.
상세보기
Sheridan, William G.; McCune, Michael E.; Pescosolido, Alessio, Flexible shaft for gas turbine engine.
상세보기
Dawson, Robert W., Fluid flow distributor apparatus for gas turbine engine mid-frame section.
상세보기
Schilling, Jan Christopher, Gas turbine engine assembly and method of assembling same.
상세보기
Orlando, Robert Joseph; Moniz, Thomas Ory, Gas turbine engine assembly and methods of assembling same.
상세보기
Walker Alan (Niskayuna NY) Staley Terrill K. (Albany NY), Gas turbines having different frequency applications with hardware commonality.
상세보기
Adamson Arthur P. (Cincinnati OH) Butler Lawrence (Cincinnati OH) Wall Robert A. (Wyoming OH), Geared counterrotating turbine/fan propulsion system.
상세보기
Law,Chi, Geartrain coupling for a turbofan engine.
상세보기
Lindemuth James E. ; Anderson William G., Heat pipe cooling for turbine stators.
상세보기
Duong, Loc; McCune, Michael E.; Dobek, Jr., Louis J., Integral sun gear coupling.
상세보기
Moniz, Thomas Ory; Carson, Scott Michael; Orlando, Robert Joseph; Lee, Ching Pang; Cherry, David Glenn, Integrated counterrotating turbofan.
상세보기
Evans, Charles R.; Ward, Douglas D., Jet aircraft fan case containment design.
상세보기
Curley Robert C. (White Marsh MD) Fisher Mark T. (Bel Air MD) Dileonardi James V. (Baltimore MD) DePinho ; Jr. A. Norton (Baldwin MD), Light weight fan blade containment system.
상세보기
Haloff ; Gary J., Method and system of controlling a jet engine for avoiding engine surge.
상세보기
Durocher, Eric; Pietrobon, John, Mid turbine frame for gas turbine engine.
상세보기
Durocher, Eric; Pietrobon, John; Nguyen, Lam, Mid turbine frame system for gas turbine engine.
상세보기
Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT), Nacelle and mounting arrangement for an aircraft engine.
상세보기
Geidel Helmut (Karlsfeld DEX) Rohra Alois (Mnchen DEX), Propfan turbine engine.
상세보기
Grieb Hubert (Germering DEX) Geidel Helmut-Arnd (Karlsfeld DEX), Propfan turbo-engine.
상세보기
Sheridan William G., Star gear system with lubrication circuit and lubrication method therefor.
상세보기
Coplin John F. (Derby GB2), Turbofan gas turbine engine.
상세보기
Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W., Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems.
상세보기
Rey Nancy M. ; Miller Robin M. ; Tillman Thomas G. ; Rukus Robert M. ; Kettle John L. ; Dunphy James R. ; Chaudhry Zaffir A. ; Pearson David D. ; Dreitlein Kenneth C. ; Loffredo Constantino V. ; Wyno, Variable area nozzle for gas turbine engines driven by shape memory alloy actuators.
상세보기

내보내기 메뉴

내보내기 구분

파일저장
인쇄
메일전송

구성항목

기본정보
상세정보

관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC

저장형식

Text(ASCII format)
Excel format
PIAS분석(.xls)

메일정보

받는사람 (필수): @
보내는사람 (선택): @
제목
내용: KISTI 검색결과 이메일 서비스

안내

총 건의 자료가 검색되었습니다.

다운받으실 자료의 인덱스를 입력하세요. (1-10,000)

검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다.

데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요)

다운로드 파일은 UTF-8 형태로 저장됩니다.
파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오.

Text(ASCII format)
Excel format

AI-Helper ※ AI-Helper는 을 사용합니다.

AI-Helper

안녕하세요, AI-Helper입니다. 좌측 "선택된 텍스트"에서 텍스트를 선택하여 요약, 번역, 용어설명을 실행하세요.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.

IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

연합인증

Gas turbine engine with high speed low pressure turbine section 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

이 특허에 인용된 특허 (31)

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	총 건의 자료가 검색되었습니다. 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오. ~ Text(ASCII format) Excel format

연합인증

Gas turbine engine with high speed low pressure turbine section 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

전체(0) 논문(0) 특허(0) 보고서(0)

전체(0) 논문(0) 특허(0) 보고서(0)

이 특허에 인용된 특허 (31)

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트