RU98123201A - GAS-TURBINE ENGINE SHAFT SEAL (OPTIONS) - Google Patents

GAS-TURBINE ENGINE SHAFT SEAL (OPTIONS)

Info

Publication number
RU98123201A
RU98123201A RU98123201/06A RU98123201A RU98123201A RU 98123201 A RU98123201 A RU 98123201A RU 98123201/06 A RU98123201/06 A RU 98123201/06A RU 98123201 A RU98123201 A RU 98123201A RU 98123201 A RU98123201 A RU 98123201A
Authority
RU
Russia
Prior art keywords
seal
casing
annular gap
vertices
axis
Prior art date
Application number
RU98123201/06A
Other languages
Russian (ru)
Other versions
RU2169846C2 (en
Inventor
Джеймс К. Кроун
Антонио Пици
Original Assignee
Прэтт энд Уитни Кэнэдэ Инк.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US08/650,441 external-priority patent/US5738490A/en
Application filed by Прэтт энд Уитни Кэнэдэ Инк. filed Critical Прэтт энд Уитни Кэнэдэ Инк.
Publication of RU98123201A publication Critical patent/RU98123201A/en
Application granted granted Critical
Publication of RU2169846C2 publication Critical patent/RU2169846C2/en

Links

Claims (11)

1. Уплотнение кожуха газотурбинного двигателя, в частности, уплотнение (24) кожуха (12) по окружности концов лопаток турбины для газотурбинного двигателя, расположенного между направленным по оси трактом горячего газа и концентрическим каналом охлаждающего газа, сформированным между кожухом (12) и внешним корпусом (32), причем кожух (12) состоит из ряда сегментов (12а... 12n), расположенных по кольцу, и каждый сегмент (12а...12n) имеет протяженную в осевом направлении платформу (14) и, по крайней мере, одно ребро (16, 18), выступающее из платформы (14) в радиальном направлении, при этом сегменты кожуха (12а...12n) имеют торцы и паз (26), выполненный в каждом торце с непрерывным переходом из части торца, соответствующей платформе в часть торца, соответствующей ребру (16, 18), отличающееся тем, что оно выполнено из однолистовой детали, которой придана форма паза (26) в торце, так что уплотнение (24) имеет часть (25, 27), направленную вдоль оси и часть (28, 30), выступающую в радиальном направлении.1. The seal of the casing of the gas turbine engine, in particular, the seal (24) of the casing (12) around the circumference of the ends of the turbine blades for the gas turbine engine located between the axially directed path of the hot gas and the concentric cooling gas channel formed between the casing (12) and the outer casing (32), moreover, the casing (12) consists of a series of segments (12a ... 12n) arranged in a ring, and each segment (12a ... 12n) has an axially extended platform (14) and at least one rib (16, 18) protruding from the platform (14) in the radial direction, while the segments of the casing (12a ... 12n) have ends and a groove (26) made in each end with a continuous transition from the end part corresponding to the platform to the end part corresponding to the edge (16, 18), characterized in that it is made of a single-sheeted part, which is shaped like a groove (26) in the end face, so that the seal (24) has a part (25, 27) directed along the axis and a part (28, 30) protruding in the radial direction. 2. Уплотнение (24) по п.1, отличающееся тем, что листовая деталь, образующая уплотнение (24), выполнена из жаропрочного материала с конфигурацией, соответствующей выступающиму ребру (16, 18), и имеет пару расходящихся стоек (28а, 28b, 30а, 30b), выполненных с возможностью упругого сжатия для плотного вхождения в паз (26) в торцах сегмента (12а...12n). 2. The seal (24) according to claim 1, characterized in that the sheet part forming the seal (24) is made of heat-resistant material with a configuration corresponding to the protruding rib (16, 18) and has a pair of diverging racks (28a, 28b, 30a, 30b), made with the possibility of elastic compression for tight fit into the groove (26) at the ends of the segment (12a ... 12n). 3. Уплотнение (24) по п.2, отличающееся тем, что оно выполнено посредством изгиба материала из жаропрочного сплава. 3. Seal (24) according to claim 2, characterized in that it is made by bending the material from a heat-resistant alloy. 4. Уплотнение (24) по п.2, отличающееся тем, что сегменты (12а...12n) кожуха (12) имеет пару разнесенных в пространстве параллельных ребер (16, 18), выступающих из платформы (14), и паз (26), выполненный непрерывным в обоих ребрах, а листовая деталь, образующая уплотнение, имеет пару параллельных, в основном идентичных, выступающих участков (28, 30), которые могут упруго сжиматься для плотного вхождения в паз (26) в торцах сегментов (12а.. .12n). 4. Seal (24) according to claim 2, characterized in that the segments (12a ... 12n) of the casing (12) have a pair of parallel-spaced apart ribs (16, 18) protruding from the platform (14), and a groove ( 26), made continuous in both ribs, and the sheet part forming the seal has a pair of parallel, mostly identical, protruding sections (28, 30) that can elastically compress to fit snugly into the groove (26) at the ends of the segments (12a. .12n). 5. Уплотнение кожуха газотурбинного двигателя, в частности, уплотнение (46) газотурбинного двигателя для герметизации соединения между двумя кольцевыми частями двигателя (12, 36), содержащего кольцевой зазор (48) с осевой составляющей (48а), имеющей противоположные разнесенные в радиальном направлении стенки, отличающееся тем, что уплотнение (46) имеет направленный вдоль оси участок (54) с волнообразной конструкцией, при этом одна вершина (60) волнообразной конструкции расположена в контакте с одной из противоположных радиально разнесенных стенок (36а) кольцевого зазора (48), а другая вершина (62) в контакте с другой стенкой (22а) кольцевого зазора (48) с герметизацией зазора (48) от утечки газов с обоих сторон соединения. 5. The seal of the casing of the gas turbine engine, in particular, the seal (46) of the gas turbine engine for sealing the connection between the two annular parts of the engine (12, 36) containing the annular gap (48) with the axial component (48a) having opposite radially spaced walls characterized in that the seal (46) has an axis-oriented portion (54) with a wave-like structure, wherein one vertex (60) of the wave-like structure is in contact with one of the opposite radially spaced walls ( 36a) of the annular gap (48), and the other apex (62) in contact with the other wall (22a) of the annular gap (48) with sealing of the gap (48) from gas leakage on both sides of the connection. 6. Уплотнение (46) по п. 5, отличающееся тем, что оно выполнено из жаропрочного упругого материала. 6. Seal (46) according to claim 5, characterized in that it is made of heat-resistant elastic material. 7. Уплотнение (46) по п. 6, отличающееся тем, что волнообразная конструкция имеет чередующиеся вершины (60, 62) с углом при вершинах, достаточным для обеспечения сжатия в радиальном направлении вершин (60, 62) и контакта вершин (60, 62) с разнесенными в радиальном направлении стенками кольцевого зазора (48) с герметизацией соединения. 7. Seal (46) according to claim 6, characterized in that the wave-like structure has alternating vertices (60, 62) with an angle at the vertices sufficient to ensure the radial compression of the vertices (60, 62) and the contact of the vertices (60, 62 ) with radially spaced walls of the annular gap (48) with a joint seal. 8. Уплотнение (46) по п. 7, отличающееся тем, что двигатель содержит корпус двигателя и кожух (12) с протяженной в радиальном направлении выступом (22), находящемся в контакте с выступом (47) крепежного элемента внутри корпуса (32) с формированием кольцевого зазора (48) между кожухом (12) и крепежным элементом (36) с осевой составляющей (48а), при этом чередующиеся вершины (60, 62) волнообразной конструкции направленного вдоль оси участка (54) уплотнения (46) имеют угол при вершинах, достаточный для обеспечения сжатия в радиальном направлении вершин (60, 62) и контакта вершин (60, 62) с разнесенными в радиальном направлении стенками (22а, 36а) кольцевого зазора (48) с герметизацией соединения между кожухом (12) и крепежным элементом (36). 8. Seal (46) according to claim 7, characterized in that the engine comprises a motor housing and a casing (12) with a radially extended protrusion (22) in contact with the protrusion (47) of the fastener inside the housing (32) with the formation of an annular gap (48) between the casing (12) and the fastener (36) with an axial component (48a), while alternating peaks (60, 62) of a wave-like design directed along the axis of the section (54) of the seal (46) have an angle at the vertices sufficient to provide compression in the radial direction of the vertices (60, 62) and contact and the vertices (60, 62) with radially spaced walls (22a, 36a) of the annular gap (48) with a sealing compound between the housing (12) and the fastening element (36). 9. Уплотнение (46) по п. 8, отличающееся тем, что кольцевой зазор содержит радиальную составляющую (48b) с противоположными разнесенными в радиальном направлении стенками, а уплотнение (46) имеет С-образный участок (52), имеющий в радиальном направлении протяженность меньшую, чем расстояние между противоположными стенками радиальной составляющей (48b) кольцевого зазора (48), а направленный вдоль оси участок (54) уплотнения имеет продолжение вдоль оси в пределах осевой составляющей (48а) кольцевого зазора (48). 9. Seal (46) according to claim 8, characterized in that the annular gap contains a radial component (48b) with opposite radially spaced walls, and the seal (46) has a C-shaped portion (52) having a radial extent smaller than the distance between the opposite walls of the radial component (48b) of the annular gap (48), and the axis of the seal portion (54) directed along the axis extends along the axis within the axial component (48a) of the annular gap (48). 10. Уплотнение (46) по п. 9, отличающееся тем, что оно выполнено из выгнутого листа жаропрочного сплава. 10. Seal (46) according to claim 9, characterized in that it is made of a curved sheet of heat-resistant alloy. 11. Уплотнение (46) по п. 10, отличающееся тем, что оно представляет собой бесконечное кольцо. 11. Seal (46) according to claim 10, characterized in that it is an infinite ring.
RU98123201/06A 1996-05-20 1997-05-20 Sealing of gas-turbine engine case (versions) RU2169846C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/650,441 1996-05-20
US08/650,441 US5738490A (en) 1996-05-20 1996-05-20 Gas turbine engine shroud seals

Publications (2)

Publication Number Publication Date
RU98123201A true RU98123201A (en) 2000-10-20
RU2169846C2 RU2169846C2 (en) 2001-06-27

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU98123201/06A RU2169846C2 (en) 1996-05-20 1997-05-20 Sealing of gas-turbine engine case (versions)

Country Status (10)

Country Link
US (3) US5738490A (en)
EP (1) EP0900323B1 (en)
JP (2) JP3947227B2 (en)
CN (1) CN1092750C (en)
CA (1) CA2255077C (en)
CZ (1) CZ292410B6 (en)
DE (1) DE69706163T2 (en)
PL (2) PL185918B1 (en)
RU (1) RU2169846C2 (en)
WO (1) WO1997044570A1 (en)

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