GB2559153A - Multi-function component for a fan or compressor section of a gas turbine engine - Google Patents
Multi-function component for a fan or compressor section of a gas turbine engine Download PDFInfo
- Publication number
- GB2559153A GB2559153A GB1701369.9A GB201701369A GB2559153A GB 2559153 A GB2559153 A GB 2559153A GB 201701369 A GB201701369 A GB 201701369A GB 2559153 A GB2559153 A GB 2559153A
- Authority
- GB
- United Kingdom
- Prior art keywords
- diaphragm
- ring portion
- annular
- fan
- compressor
- Prior art date
- Legal status (The legal status 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 status listed.)
- Withdrawn
Links
- 239000000463 material Substances 0.000 claims abstract description 16
- 230000008602 contraction Effects 0.000 claims abstract description 12
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 230000015572 biosynthetic process Effects 0.000 claims description 7
- 238000005755 formation reaction Methods 0.000 claims description 7
- 239000007769 metal material Substances 0.000 claims description 5
- 239000002990 reinforced plastic Substances 0.000 claims description 4
- 239000004033 plastic Substances 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000001141 propulsive effect Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A multi-function component for a fan or compressor of a gas turbine engine has an annular diaphragm 32 that partially bridges a gap between a row of stator vanes and an axially adjacent row of fan or compressor blades to form a non-rotatable, radially inner wall portion of the working gas annulus. The component has a ring portion 33 carrying an annular seal 34 which forms one half of an air seal with a corresponding annular seal which rotates with the rotating stage. The diaphragm and ring portion are formed of dissimilar materials, which may have different coefficients of thermal expansion, and where the diaphragm may be plastic composite, and the ring may be metallic. The diaphragm and ring portion are connected at an annular joint that prevents air leakage therethrough but which accommodates differential thermal expansion and contraction. The joint may comprise an annular slot 35 and annular tenon 36, and there may be an annular compliant member 39 that connects the diaphragm to the ring. Also claimed is a fan or compressor comprising the component, a gas turbine engine, and the annular diaphragm and ring portion respectively.
Description
(54) Title of the Invention: Multi-function component for a fan or compressor section of a gas turbine engine Abstract Title: Thermal expansion accommodating seal for a gas turbine engine (57) A multi-function component for a fan or compressor of a gas turbine engine has an annular diaphragm 32 that partially bridges a gap between a row of stator vanes and an axially adjacent row of fan or compressor blades to form a non-rotatable, radially inner wall portion of the working gas annulus. The component has a ring portion 33 carrying an annular seal 34 which forms one half of an air seal with a corresponding annular seal which rotates with the rotating stage. The diaphragm and ring portion are formed of dissimilar materials, which may have different coefficients of thermal expansion, and where the diaphragm may be plastic composite, and the ring may be metallic. The diaphragm and ring portion are connected at an annular joint that prevents air leakage therethrough but which accommodates differential thermal expansion and contraction. The joint may comprise an annular slot 35 and annular tenon 36, and there may be an annular compliant member 39 that connects the diaphragm to the ring. Also claimed is a fan or compressor comprising the component, a gas turbine engine, and the annular diaphragm and ring portion respectively.
1/4
Fig. 1
2/4
Fig. 2
3/4
Fig. 3C
4/4
Fig. 4
Fig. 5
MULTI-FUNCTION COMPONENT FOR A FAN OR COMPRESSOR SECTION OF A GAS
TURBINE ENGINE
Field of the Invention
The present invention relates to a multi-function component for a fan or compressor section of a gas turbine engine.
Background
Figure 1 shows schematically a longitudinal cross-section through a portion of a conventional low pressure compressor of a gas turbine engine. The compressor has alternating rows of compressor blades and stator vanes. Between a front row 101 of the stator vanes (the variable inlet guide vanes) and the following row 100 of compressor blades, an annular diaphragm 102 forms a radially inner wall portion of the working gas annulus of the compressor. More particularly, the diaphragm extends from a bolting position radially inwards of the stator vanes to a trailing edge which is spaced a short distance in front of leading edges of radially inner platforms of the blades.
A labyrinth air seal prevents excessive air leakage through this spacing. To form this air seal, a ring portion 103, which is unitarily formed with the annular diaphragm 102, is located radially inwards of the trailing edge of the diaphragm. The ring portion carries an annular seal 104 which forms one half of the labyrinth air seal. The other half of the labyrinth air seal is carried by an extension from a rotor disc 105 on which the compressor blades are mounted.
The unitary diaphragm-ring portion component is manufactured from a single material that has sufficient structural strength and accommodates required thermal movements. The ring portion and diaphragm are designed to withstand pressure differentials across the structure and to avoid or reduce vibration. This can result in a design that does not provide the radial thermal movements needed to provide an optimal seal.
Summary
Accordingly, in a first aspect the present invention provides a multi-function component for a fan or compressor of a gas turbine engine, the multi-function component having:
an annular diaphragm which is configured such that, in use, it at least partially bridges a gap between a circumferential row of stator vanes of the fan or compressor and an axially adjacent, circumferential row of fan or compressor blades to form a non-rotatable, radially inner wall portion of the working gas annulus of the fan or compressor; and a ring portion carrying an annular seal which is configured such that, in use, the annular seal forms one half of an air seal with a corresponding annular seal which rotates with the row of fan or compressor blades;
wherein the diaphragm and the ring portion are formed of dissimilar materials, the diaphragm and the ring portion being connected at an annular joint which is configured to prevent air leakage therethrough but which accommodates differential thermal expansion and contraction of the diaphragm and the ring portion.
Thus by the provision of the annular joint it becomes possible separate the functionality of the diaphragm from that of the ring portion. In particular, it allows the formation of the diaphragm and the ring portion from dissimilar materials. In this way, for example, the ring portion can be made of a material with a different coefficient of thermal expansion than that of the diaphragm, and thus the ring portion can better seal to the movements of the other half of the air seal. Similarly, the diaphragm can better perform its structural function.
In a second aspect, the present invention provides a fan or compressor of a gas turbine engine, the fan or compressor having:
a circumferential row of stator vanes, an axially adjacent, circumferential row of fan or compressor blades, and the multi-function component of any one of the previous claims, wherein the annular diaphragm of the component at least partially bridges a gap between the row of stator vanes and the row of fan or compressor blades to form a non-rotatable, radially inner wall portion of the working gas annulus of the fan or compressor, and the annular seal of the ring portion of the component forms one half of an air seal with a corresponding annular seal which rotates with the row of fan or compressor blades.
In a further aspect, the present invention provides a gas turbine engine having the fan or compressor of the second aspect.
In a further aspect, the present invention provides the annular diaphragm of the multifunction component of the first aspect.
In a further aspect, the present invention provides the ring portion of the multi-function component of the first aspect.
Optional features of the invention will now be set out. These are applicable singly or in any combination with any aspect of the invention.
The differential thermal expansion and contraction accommodated by the joint is typically differential thermal expansion and contraction in the radial direction.
The diaphragm may be formed of a material having one (i.e. relatively low or relatively high) coefficient of thermal expansion, and the ring portion may be formed of a material having a different coefficient of thermal expansion. Additionally or alternatively, the thermal inertias of the diaphragm and the ring portion can be different, producing different expansion/contraction rates for the two parts of the component.
The diaphragm may be formed of a reinforced plastic composite material, such as a carbon fibre reinforced composite (CFRP), or a glass fibre reinforced composite (GFRP). Such materials are strong and light, but have relatively low coefficients of thermal expansion. However, reinforced plastic composite materials are not conventionally used for fan or compressor seal structures as their low coefficients of thermal expansion tend not to accommodate the thermal growth of a typical disc or rotor.
The ring portion may be formed of a metallic material, such as a steel, a titanium alloy or a nickel-based alloy. Such materials have relatively high coefficients of thermal expansion.
The material of the ring portion may have a coefficient of thermal expansion which is matched to that of the material of the corresponding annular seal.
Typically the ring portion may be located radially inwards of the diaphragm. The corresponding annular seal may be carried by a rotor ring on which the row of fan or compressor blades is mounted. The air seal may be a labyrinth air seal. The stator vanes can variable or static stator vanes.
Conveniently, the joint may comprise an annular slot formed by one of the diaphragm and the ring portion, and an annular tenon formed by the other of the diaphragm and the ring portion and received in the slot, wherein the tenon seals against a side surface of the slot to prevent air leakage through the joint, and wherein the tenon is slidingly movable in the slot to accommodate the differential thermal expansion and contraction. For example, the annular slot may be formed by the diaphragm and the annular tenon may be formed by the ring portion.
The diaphragm and the ring portion may further have respective formations which interengage with each other to centralise the ring portion on the diaphragm and to prevent relative rotation of the diaphragm and the ring portion at the annular joint. For example, the formations may be one or more keys formed by one of the diaphragm and the ring portion, and respective matching recesses formed by the other of the diaphragm and the ring portion and in which the keys engage. The keys and recesses may be circumferentially distributed around the component, e.g. 90° apart.
The joint may comprise an annular compliant member that connects the diaphragm to the ring portion, the compliant member preventing air leakage through the joint and flexing to accommodate the differential thermal expansion. Such a compliant member may be used in addition to the above-mentioned slot and tenon structure. For example, the compliant member may be a bellows.
Brief Description of the Drawings
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:
Figure 1 shows a longitudinal cross-section through a portion of a conventional low pressure compressor of a gas turbine engine;
Figure 2 shows a longitudinal cross-section through a ducted fan gas turbine engine;
Figure 3 shows schematically (A) a longitudinal cross-section including radial direction R-R through a trailing edge end of a diaphragm and a ring portion of a multi-function component of a compressor, (B) a different longitudinal cross-section including radial direction R’-R’ through the trailing edge end of the diaphragm and the ring portion, R’-R’ being angularly spaced from but on the same transverse section as R-R, (C) a forward-facing view of the diaphragm and the ring portion on the transverse cross-section which includes R-R and R’R’, and (D) a perspective view of a part of the ring portion;
Figure 4 shows schematically a longitudinal cross-section through a trailing edge end of a diaphragm and a ring portion of a further multi-function component of a compressor; and
Figure 5 shows schematically a longitudinal cross-section through a trailing edge end of a diaphragm and a ring portion of another multi-function component of a compressor.
Detailed Description and Further Optional Features
With reference to Figure 2, a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate-pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediatepressure compressor 13 compresses the air flow A directed into it before delivering that air to the high-pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate-pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
Between a front row of the stator vanes of the intermediate-pressure compressor 13 and the following row of compressor blades, a multi-function component provides an annular diaphragm which forms a radially inner wall portion of the working gas annulus of the compressor. The diaphragm extends from a bolting position radially inwards of the stator vanes to a trailing edge which is spaced a short distance in front of leading edges of radially inner platforms of the blades.
Figure 3 shows schematically (A) a longitudinal cross-section including radial direction R-R through a trailing edge end of the diaphragm 32 and a ring portion 33 of the multi-function component, (B) a different longitudinal cross-section including radial direction R’-R’ through the trailing edge end of the diaphragm and the ring portion, R’-R’ being angularly spaced from but on the same transverse section as R-R, (C) a forward-facing view of the diaphragm and the ring portion on the transverse cross-section which includes R-R and R’-R’, and (D) a perspective view of a part of the ring portion.
The ring portion 33 carries an annular seal 34 which forms one half of a labyrinth air seal with a corresponding annular seal which is mounted to an extension from the rotor disc on which the compressor blades are mounted. The air seal can prevent the air being compressed by the intermediate-pressure compressor 13 escaping from the working gas annulus of the engine. Alternatively, the air seal can prevent higher pressure air leaking into the compressor.
The diaphragm 32 and the ring portion 33 of the multi-function component are formed as two separate sub-components from dissimilar materials. In particular, the diaphragm can be formed of a reinforced plastic composite material (such as CFRP or GFRP) or a metallic material which may be different to the metallic material of the rotor disc from which the corresponding annular seal is mounted. The ring portion may be formed from a similar metallic material to that of the rotor disc from which the corresponding annular seal is mounted. In this way, the ring portion can have a coefficient of thermal expansion which, if not matched to that of the rotor disc, is such that the labyrinth air seal maintains good sealing performance. On the other hand, the diaphragm can be better optimised to provide a high strength to weight ratio.
An annular joint is provided between the diaphragm 32 and the ring portion 33, the joint accommodating differential thermal expansion and contraction of the diaphragm and the ring portion while avoid leakage therethrough. For example, as shown in Figures 3A-D, the joint may comprise an annular slot 35 formed by the diaphragm and an annular tenon 36 formed by the ring portion. As best shown in Figure 3B, the tenon is received in the slot and seals against a side surface of the slot (the left hand surface as drawn in Figure 3B) to prevent air leakage through the joint. The diaphragm may be axially splittable to allow assembly. The split can be fastened (e.g. bolted) together after the ring portion is in position. However, the tenon is slidingly movable in the slot in the radial direction and thereby accommodates the differential thermal expansion and contraction.
As shown in Figures 3A, C and D, the joint also has centring and anti-rotation formations provided by four circumferentially equidistantly-spaced keys 37 formed by the ring portion 33 and matching recesses 38 formed by the diaphragm 32. The keys engage with the recesses to ensure the centrelines of the ring portion and diaphragm are coincident, and to prevent the ring portion rotating relative to the diaphragm, while still permitting relative radial movement.
Variations on the annular joint shown in Figures 3A-D are possible. For example, the slot 35 can be formed by the ring portion 33 and the tenon 36 by the diaphragm 32. As another example, the keys 37 can be formed by the diaphragm and recesses 38 formed by the ring portion. Also differing numbers and spacings of the keys and recess may be used. The keys and recesses may be on different parts of the ring portion and diaphragm - for example rather than forming the keys with the tenon 36 so that they locate within the slot 35, they could be to the rear or the front of the diaphragm.
Figure 4 shows schematically a longitudinal cross-section through the trailing edge end of the diaphragm 32 and the ring portion 33 to illustrate another variant joint. In this case the joint is supplemented by an annular bellows 39 that connects the diaphragm to the ring portion. The bellows flexes to accommodate the differential thermal expansion and contraction, and also helps to seal the joint.
Indeed, the bellows 39 is just one example of a more general annular compliant member that can seal the joint and preferably also prevents relative rotation of the ring portion 33 and the diaphragm 32. Figure 5 shows schematically a longitudinal cross-section through the trailing edge end of the diaphragm 32 and the ring portion 33 to illustrate a further variant joint. In this case an annular compliant member in the form of a compliant “arm” 40 extends from the diaphragm to the ring portion. The seal effected by the compliant member can be sufficient on its own such that the slot 35 and tenon 36 arrangement may not be needed. However, centring formations may still be required.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
Claims (12)
1. A multi-function component for a fan or compressor of a gas turbine engine, the multi-function component having:
an annular diaphragm (32) which is configured such that, in use, it at least partially bridges a gap between a circumferential row of stator vanes of the fan or compressor and an axially adjacent, circumferential row of fan or compressor blades to form a non-rotatable, radially inner wall portion of the working gas annulus of the fan or compressor; and a ring portion (33) carrying an annular seal which is configured such that, in use, the annular seal forms one half of an air seal with a corresponding annular seal which rotates with the row of fan or compressor blades;
wherein the diaphragm and the ring portion are formed of dissimilar materials, the diaphragm and the ring portion being connected at an annular joint which is configured to prevent air leakage therethrough but which accommodates differential thermal expansion and contraction of the diaphragm and the ring portion.
2. The component according to claim 1, wherein the diaphragm is formed of a material having one coefficient of thermal expansion, and the ring portion is formed of a material having a different coefficient of thermal expansion.
3. The component according to claim 1 or 2, wherein the diaphragm is formed of a reinforced plastic composite material, and the ring portion is formed of a metallic material.
4. The component according to any one of the previous claims, wherein the joint comprises an annular slot (35) formed by one of the diaphragm and the ring portion, and an annular tenon (36) formed by the other of the diaphragm and the ring portion and received in the slot, wherein the tenon seals against a side surface of the slot to prevent air leakage through the joint, and wherein the tenon is slidingly movable in the slot to accommodate the differential thermal expansion and contraction.
5. The component according to any one of the previous claims, wherein the diaphragm and the ring portion further have respective formations which inter-engage with each other to centralise the ring portion on to the diaphragm and to prevent relative rotation of the diaphragm and the ring portion at the annular joint.
6. The component according to claim 5, wherein the formations are one or more keys (37) formed by one of the diaphragm and the ring portion, and respective matching recesses (38) formed by the other of the diaphragm and the ring portion and in which the keys engage.
7. The component according to any one of the previous claims, wherein the joint comprises an annular compliant member that connects the diaphragm to the ring portion, the
5 compliant member preventing air leakage through the joint and flexing to accommodate the differential thermal expansion.
8. The component according to claim 7, wherein the compliant member is a bellows (39) .
9. A fan or compressor of a gas turbine engine, the fan or compressor having:
10 a circumferential row of stator vanes, an axially adjacent, circumferential row of fan or compressor blades, and the multi-function component of any one of the previous claims, wherein the annular diaphragm of the component at least partially bridges a gap between the row of stator vanes and the row of fan or compressor blades to form a non-rotatable, radially inner wall portion of
15 the working gas annulus of the fan or compressor, and the annular seal of the ring portion of the component forms one half of an air seal with a corresponding annular seal which rotates with the row of fan or compressor blades.
10. A gas turbine engine having the fan or compressor of claim 9.
11. The annular diaphragm of the multi-function component according to any one of
20 claims 1 to 8.
12. The ring portion of the multi-function component according to any one of claims 1 to 8.
Application No: GB1701369.9
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1701369.9A GB2559153A (en) | 2017-01-27 | 2017-01-27 | Multi-function component for a fan or compressor section of a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1701369.9A GB2559153A (en) | 2017-01-27 | 2017-01-27 | Multi-function component for a fan or compressor section of a gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201701369D0 GB201701369D0 (en) | 2017-03-15 |
| GB2559153A true GB2559153A (en) | 2018-08-01 |
Family
ID=58462687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1701369.9A Withdrawn GB2559153A (en) | 2017-01-27 | 2017-01-27 | Multi-function component for a fan or compressor section of a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2559153A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2551492A1 (en) * | 2010-03-24 | 2013-01-30 | Kawasaki Jukogyo Kabushiki Kaisha | Seal structure for turbine rotor |
| FR2991404A1 (en) * | 2012-05-31 | 2013-12-06 | Snecma | Fixed part for labyrinth seal device for open rotor turbomachine e.g. turbojet, has intermediate piece between support portion and wear part, where thermal expansion coefficient of intermediate piece is greater than that of support portion |
| US20140227088A1 (en) * | 2011-09-07 | 2014-08-14 | Herakles | Assembly formed by a turbine nozzle or a compressor diffuser made of cmc for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly |
| GB2540233A (en) * | 2015-03-02 | 2017-01-11 | Rolls Royce Plc | Seal arrangement |
-
2017
- 2017-01-27 GB GB1701369.9A patent/GB2559153A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2551492A1 (en) * | 2010-03-24 | 2013-01-30 | Kawasaki Jukogyo Kabushiki Kaisha | Seal structure for turbine rotor |
| US20140227088A1 (en) * | 2011-09-07 | 2014-08-14 | Herakles | Assembly formed by a turbine nozzle or a compressor diffuser made of cmc for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly |
| FR2991404A1 (en) * | 2012-05-31 | 2013-12-06 | Snecma | Fixed part for labyrinth seal device for open rotor turbomachine e.g. turbojet, has intermediate piece between support portion and wear part, where thermal expansion coefficient of intermediate piece is greater than that of support portion |
| GB2540233A (en) * | 2015-03-02 | 2017-01-11 | Rolls Royce Plc | Seal arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201701369D0 (en) | 2017-03-15 |
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