Field of the invention
[0001] The invention relates to a turbomachine (or rotating machine) component, particularly
a gas turbine engine component in a hot region of a gas turbine engine, in which a
hot wall is cooled via a corrugated surface.
Background of the invention
[0002] Gas turbine engines like other rotating machines comprise sections wherein a cool
fluid is guided and other regions in which a hot fluid is guided through the engine.
In the gas turbine engine typically ambient air as a fairly cool fluid may be compressed
by a compressor section and provided to a combustor in which the substantially cool
fluid (at least cooler than the working conditions within the combustor) will be burned
together with fuel to provide a driving force for a subsequent turbine section - an
expansion turbine - in which a hot fluid from the combustor will drive rotor blades
of the turbine to drive again a shaft. The compressed air will also be used to cool
hot engine parts, particularly in the combustor or expansion turbine section.
[0003] In the combustor or in the downstream sections past the combustor hot temperatures
can occur on components that are guiding the hot fluid through the gas turbine engine.
The temperatures can be up to 1,500 °C. Nevertheless, materials used typically in
a gas turbine engine cannot withstand temperatures above 800 °C. Therefore, these
components may need to be cooled or a specific coating is required to protect the
component. Cooling may be implemented in a way that a fraction of the air or the fluid
from the compressor is extracted - i.e. branched off from a main fluid path - and
guided to the component which needs to be cooled. Cooling then can be performed at
the to be cooled part by different measures, for example impingement cooling, film
cooling, effusion cooling, transpiration cooling and/or convection cooling.
[0004] The provision of cooling functionality on the other hand reduces the efficiency of
the gas turbine engine. Therefore it is the goal to limit the cooling as much as possible
so that the efficiency does not downgrade and is maximised. It needs to be considered
though, that the lifetime of the component depends largely on the conditions such
that the component will not experience a temperature that goes above a designed temperature
level.
[0005] The temperature level experienced by a component may vary at different locations
of the component. For example an upstream region of a combustion liner wall may experience
hotter temperatures than a downstream region of the same combustion liner. Therefore,
the downstream region may not require the same amount of cooling as the upstream region.
On the other hand, a cooling channel of a specific length may be more efficient at
a first end of the cooling passage assuming the cooling air may be cooler at the first
end than at a downstream end of the cooling passage, because the cooling air has taken
the heat from the to be cooled component which is resulting in a temperature rise
of the cooling air.
[0006] Components to be cooled in a gas turbine engine are mainly located at a combustion
chamber, an expansion turbine section, a transition piece in between, or possibly
at an exhaust.
[0007] One known technology to improve cooling of a component that experiences thermal energy
or thermal heat is to provide ribs or other protrusions onto one side of the component
along which cooling fluid is guided, with the effect of a better heat transfer so
that in consequence the material of the component is cooled.
[0008] Depending on the size or shape of the component specific production methods may be
applied to generate turbulators, e.g. casting to create ribs on internal surfaces
inside hollow blades, welding or brazing onto external surfaces, or machining off
material from a component to create turbulators as a residual at the surface.
[0009] Dependent upon the design of the individual component, manufacturing of turbulators
- like ribs - at a surface of that component can require a lot of effort during production
of the component.
Summary of the invention
[0010] The present invention seeks to provide an improved way of providing an alternative
to a rib structure with rectangular shape for a cooling side of hot components in
a gas turbine engine or other turbomachines or rotating machines or even other machines
that experience life-limiting temperatures. Particularly the invention reduces also
the manufacturing efforts and manufacturing time.
[0011] This objective is achieved by the independent claims. The dependent claims describe
advantageous developments and modifications of the invention.
[0012] The invention is directed to a turbomachine component (or rotating machine component),
arrangeable in a turbomachine like a gas turbine engine, wherein the turbomachine
component is built in parts from a curved or planar panel, the panel comprising a
first surface and a second surface. The turbomachine component is arrangeable such
that, during operation of the turbomachine, the first surface - and consequently the
panel - is affected by thermal radiation, i.e. thermal heat.
[0013] The second surface is affected by a cooling fluid travelling along the second surface,
particularly to cool the panel. The second surface comprises a plurality of alternating
elongated depressions and elongated elevations, wherein the depressions are formed
each as an elongated concave groove.
[0014] Thus, a corrugated wall is provided of a specific shape to support convective cooling.
[0015] The invention is advantageous as the shape of the surface provides good cooling properties.
And additionally the form of elongated concave grooves allows easy manufacturing,
as a single one of the concave grooves can be machined off in a single pass by a milling
tool without the need to equip the milling tool with different set of cutters. A single
cutter may be used to mill the concave shape of a section of the elongated concave
groove.
[0016] In a cross section, the concave shape is a section of an ellipse. In a specific embodiment,
the shape may be a section of a circle. An ellipse or a circle can be created by a
rotating milling cutter about a rotating axis; an ellipse can be formed if the rotating
milling cutter is angled compared to the direction of relative movement of the milling
cutter in respect of the panel.
[0017] A circle can be formed if the rotating axis of the milling cutter is perpendicular
to the to be generated elongated groove. Thus, the concave groove follows in cross-section
a shape of a part of an arc of a circle when the cross-section is taken from a direction
perpendicular to ridges of one of the elevations.
[0018] The component may particularly be located in a combustion chamber, in a burner section,
in a transition duct or in a turbine section of a gas turbine engine. Possibly it
may also be located at a casing or at an exhaust of a gas turbine engine. The depressions
and elevations on the second surface are present to provide cooling of the component
which is affected by the hot-working media - in general: affected by thermal energy
- which is in contact with at least one surface of the component, specifically the
first surface. The cooling fluid may particularly be air taken from a compressor section
of a gas turbine engine. But other sources of cooling fluid could be used, e.g. ambient
air. The cooling fluid may be pressurised.
[0019] In case of a combustion chamber part, the component may be for example a combustion
chamber liner. Such a combustion chamber liner may itself be curved. Therefore, in
case the panel is curved, the concave groove forms a segment of skewed circular cylindrical
recess following a contour of the panel.
[0020] In gas turbine engines most components are formed such that they are arranged cylindrically
about a main axis of the gas turbine engine. E.g. heat shields may be segments of
a full cylindrical surface. But each segment may be considered substantially flat
or planar. In case the panel is planar or substantially planar, the concave groove
forms a segment of circular cylindrical recess.
[0021] Preferably the first surface is free of elevations and recesses. In case of a panel
being substantially planar, also the first surface is preferably planar.
[0022] As already said, the depressions may be manufactured by machining the depressions
into the second surface. Under machining a process is understood that removes surface
material from a component, particularly milling.
[0023] The depressions may be manufactured by machining the depressions into the second
surface via a milling cutter, wherein one of the milling cutter and the second surface
follows a rotation along a circular arc section. Additionally the milling cutter or
the second surface will be moved continuously or step-wise in direction of the elongation
of the elongated concave groove to machine off an expanded surface section. Eventually
an elongated groove is generated.
[0024] Several milling cutters will machine off several grooves in parallel time. Alternatively
after a complete groove is created, the panel will be repositioned so that a further
groove can be created.
[0025] In an embodiment the elevations may form a ridge, preferably with a substantial flat
surface. In this case the elevations may form a leveled ridge.
[0026] The ridges of the elevations may be arranged substantially parallel to another.
[0027] Furthermore the ridges of the elevations may be arranged substantially perpendicular
to a flow direction of a cooling fluid along the second surface during operation of
the turbomachine.
[0028] Selecting a geometry of the second surface and the orientation in respect of the
expected cooling fluid flow direction allows that no film of cooling fluid attaches
to the second surface, which would counteract the cooling effect for the hot panel.
[0029] Also an angled orientation of the grooves and elevations in respect of the expected
cooling fluid flow may be advantageous. Thus, ridges of the elevations may be arranged
angled to a flow direction of the cooling fluid along the second surface during operation
of the turbomachine, wherein an angle of attack of the cooling fluid onto the ridges
is between -60° and +60° in respect of a direction perpendicular to the ridges. Possibly
also advantageous are also angles between -30° and +30°. The direction perpendicular
to the ridges is defined by 0°.
[0030] Obviously the angles can also be taken between a direction of the cooling fluid flow
and an orientation of the ridges, which will be called in the following as angle of
attack. An angle of attack of 90° refers to a cooling fluid being perpendicular to
the main expanse of the ridges. By this definition a preferred angle of attack may
be between 30° and 90°. Possibly also advantageous are also angles of attack between
60° and 90°. Particularly, in one embodiment, the cooling fluid may be angled, that
means that the 90° orientation may be excluded from the previously mentioned ranges.
[0031] The depressions and the elevations may be sized and oriented to act as turbulators
for the cooling fluid during operation of the turbomachine.
[0033] The location and/or size and/or orientation of the depressions and elevations will
allow specific adaptations to temperature circumstances, to increase or decrease a
cooling effect.
[0034] A top level surface of the ridge may have a homogeneous height, i.e. defining a levelled
top surface. The levelled top surface (31) of the levelled ridge may be parallel to
the first surface or to the second surface prior to the machining of the second surface.
[0035] As previously indicated the invention may be applied to a component in which the
panel is located in a hot region of the gas turbine engine. Particularly the panel
is at least one of: a combustion chamber wall, a combustion chamber liner, a transition
duct downstream of a combustion chamber, a heat shield, an expansion turbine intermediate
duct, an exhaust nozzle of an expansion turbine, and a casing.
[0036] Manufacturing methods may be slightly different, dependent on the shape of the component.
To generate a fraction of a concave groove which later can be extended to an elongated
concave groove a panel - or the turbomachine comprising the panel - without substantial
surface structure - i.e. being flat or planar, possibly following a general curvature
- will be provided to a milling machine. According to the invention a manufacturing
process is performed in which a section of a depression is cut into the second surface
of the panel. This cutting is performed by rotating the milling cutter and/or the
turbomachine component relative to another such that the milling cutter machines a
segment of a concave groove, particularly a segment of a circular cylindrical groove,
into the second surface.
[0037] To complete an elongated groove the panel will be repositioned afterwards in a repetitive
way - in a first direction -, each time followed by the previously mentioned cutting
step, so that a continuous groove is generated.
[0038] To generate more than a single groove several cutters will be operated that way at
the same time, or the panel will be repositioned such that performing the previously
mentioned steps would create a further groove parallel to the already machined groove(s).
[0039] Several of the grooves may be substantially parallel and equidistant. The geometry
of parallel grooves and parallel elevations may be identical to another.
[0040] The panel, throughout this document, is a component with a major expanse following
a planar or curved plane and with a minor expanse in a perpendicular direction. Preferably
it may be built from sheet metal or at least would follow a shape of a typical sheet
metal.
[0041] The base material may also be a cast component with similar geometry like a sheet
metal, i.e. comprising at least a subcomponent in form of a panel.
[0042] Such a sheet metal or a panel is frequently used for components to guide hot fluids
through a channel and/or to separate hot fluids from surroundings. Additionally sheet
metals and panels may be used to apply cooling onto one of its surfaces.
[0043] Hot fluids typically are combusted products, e.g. a mixture of air and fuel after
combustion.
[0044] Cooling fluids are typically compressed air, compressed by a compressor of a gas
turbine engine or by a separate compressor. Cooling air as cooling fluid can be provided
from the compressor via pipes or via some kind of passages or channels within a casing.
After the cooling air has been passed the second surface it may be released via passages
into the hot working media stream.
[0045] The cooling effect generally is driven by the heat transfer coefficient, the temperature
difference and the contact area between a metal component and cooling air along the
cooled second surface. Besides the discussed convectional cooling from one side of
a panel, possibly other methods of cooling may also be present in the same component,
e.g. incorporated cooling channels within sub-sections of the component. It may worth
noticing that the heat transfer coefficient is generally also dependent on the cooling
air velocity. Also a boundary layer of air - a kind of air cushion - may counteract
the cooling effect, while a cushion of air at the hot side surface may be beneficial
as leading to film cooling.
[0046] When in explaining the features of the invention reference is taken to cross sectional
areas, it needs to be understood that generally a cross section is taken at a plane
defined by (a) a vector defining a shortest distance between adjacent elevations and
(b) a vector perpendicular to the first surface. The vector defining a shortest distance
between adjacent elevations may substantially also be a main direction of a cooling
fluid flow.
[0047] The discussed component may be a complex three dimensional component. Nevertheless,
it may have at least a section in which it has a plate-like or panel-like appearance,
possibly curved around a hot working gas passage, e.g. an annular or cylindrical combustion
chamber or an annular passage through an expansion turbine. A panel or plate may be
a solid element but may also be built from a sheet metal and formed into the wanted
shape. The panel may only define a segment of an annular passage and several of these
define the complete annular passage.
[0048] The component may be built preferably from metal or any other heat conductive chemical
element.
[0049] As already indicated, the invention is directed to a turbomachine component and also
to a manufacturing method to produce such a turbomachine component. Furthermore, the
invention is also related to a turbomachine which includes such a turbomachine component.
Specifically, the invention is also directed to a gas turbine engine including such
component.
[0050] It has to be noted that embodiments of the invention have been described with reference
to different subject matters. In particular, some embodiments have been described
with reference to apparatus type claims whereas other embodiments have been described
with reference to method type claims. Some effects may only be realized during operation
of the apparatus. However, a person skilled in the art will gather from the above
and the following description that, unless otherwise notified, in addition to any
combination of features belonging to one type of subject matter also any combination
between features relating to different subject matters, in particular between features
of the apparatus type claims and features of the method type claims is considered
as to be disclosed with this application.
[0051] The aspects defined above and further aspects of the present invention are apparent
from the examples of embodiment to be described hereinafter and are explained with
reference to the examples of embodiment.
Brief description of the drawings
[0052] Embodiments of the invention will now be described, by way of example only, with
reference to the accompanying schematical drawings, of which:
- FIG. 1:
- shows a longitudinal section of a section of a combustion chamber;
- FIG. 2:
- shows a magnified view of the detail V of figure 1;
- FIG. 3:
- illustrates an angled view of s segment of a combustion chamber liner with the given
surface structure according to the invention;
- FIG. 4:
- illustrates how the machining is performed at a conical component;
- FIG. 5:
- shows a magnified view about the relation between the machining tool and the machined
surface.
[0053] The illustrations in the drawings are schematical. It is noted that for similar or
identical elements in different figures, the same reference signs will be used to
denote the same or equivalent features.
[0054] Some of the features and especially the advantages will be explained for an assembled
gas turbine, but obviously the features can be applied also to single components of
the gas turbine but may show the advantages only once assembled and during operation.
But when explained by means of a gas turbine during operation none of the details
should be limited to a gas turbine solely while in operation. As the invention is
inspired to counteract problems of temperatures in consequence of combustion processes,
the features can also applied to different types of machines that experience high
temperatures.
Detailed description of the invention
[0055] A gas turbine engine may serve as one example of a turbomachine. The gas turbine
- short for gas turbine engine - comprises an air inlet at one end followed by a compressor
stage in which incoming air is compressed for application to one or more combustors
as combustion devices, which may be annular or so-called can-annular or silo type,
the can-annular ones being distributed circumferentially around the turbine axis.
Fuel is introduced into the combustors and mixed in there with a major part of the
compressed air taken from the compressor. Hot gases with high velocity as a consequence
of combustion in the combustors are directed to a set of turbine blades within a turbine
section, being guided (i.e. redirected) by a set of guide vanes. The turbine blades
and a shaft - the turbine blades being fixed to that shaft - form the rotor and are
rotated about an axis as a result of the impact of the flow of the hot gases. The
rotating rotor also is equipped with blades of a compressor stage and therefore also
rotates blades of the compressor stage, with the consequence that the compressed air
supply to the combustors is provided by these rotating compressor blades (due to interaction
of rotating compressor blades with stationary compressor vanes) once in operation.
There may be more than one rotor in the gas-turbine engine.
[0056] Figure 1 shows a cross sectional view of a part of a combustor section of a gas turbine
engine representing a turbomachine 1, particularly a cross section of a combustion
chamber 105. The combustion chamber 105 may for example be annular or can-annular
(i.e. formed by a plurality of combustor cans all arranged about an axis of the gas
turbine engine). A burner 106 may be present at an upstream end of the combustion
chamber 105. The combustion chamber 105 is depicted in a way that the main fluid flow
100 of combusted products is in right hand direction in the drawing plane. The burner
106 is only depicted in an abstract way.
[0057] The cross section is taken through an axis of rotation X of the gas turbine engine,
particularly - in case of an annular combustor - through an axis of rotation X of
annular combustor. A radial direction may be defined in a direction perpendicular
to the axis of rotation.
[0058] The combustion chamber 105, particularly its liner, as a turbomachine component 10
is shown in a cross sectional view. According to figure 1 a double shell liner is
shown, with an outer wall 101 and an inner wall 102 ("inner" and "outer" in respect
of the combustion chamber 105). The combustion chamber will house a flame generating
thermal radiation 23. Cooling fluid 24, i.e. particularly compressed air provided
from the compressor of the gas turbine, is traveling at the outside of the combustion
chamber liner through a liner passage 103. The cooling fluid flow direction may be
different depending on the spot of location. One direction of the cooling fluid flow
at a specific location is indicated by an arrow with the reference numeral 24.
[0059] The turbomachine component 10 may have at least one panel 11, i.e. the inner wall
102 of the combustion chamber liner, comprising a first surface 21 and a second surface
22. In case of an annular combustion chamber a radial inwards and a radial outwards
liner wall (inwards liner wall 102' and outwards liner wall 102") may each comprise
a panel 11 according to the invention.
[0060] The turbomachine component 10 may be a complex three dimensional structure. The panel
11 may be curved in axial direction X (like indicated in the cross section of FIG.
1 at a downstream end of the liner) and also curved around the path for the working
media in circumferential direction or curved around the axis of rotation X. Nevertheless
you could consider the panel 11 as being planar, particularly if you analyse just
a sub section of the overall component. The panel 11 may substantially be fairly thin
material, i.e. with larger expanse in two directions and small expanse in width. Particularly
a curved or contoured plate-like panel 11 may be made from sheet metal and formed
into the desired form. It may also be a cast component.
[0061] The second surface 22 of the panel 11 is also shown in the figure and is directed
to a cooled side, i.e. facing a cooling air cavity - in the figure the liner passage
103 - for guiding the cooling fluid 24, the cooling air cavity surrounding the combustion
chamber 105. The opposite surface of the panel 11 is the first surface 21 and is facing
the hot working media within the combustion chamber 105.
[0062] Within the combustion chamber 105, during operation, air and fuel is combusted generation
thermal radiation 23, leading to heating up the panel 11. The main source of thermal
radiation 23 may be a flame at an upstream end of the combustion chamber 105. At this
upstream end - at least at the upstream end, maybe along the full length or most of
the length of the inner wall 102 or alternatively just limited to the upstream end
- it may be advantageous to provide cooling elements at the second surface 22. According
to the invention the second surface 22 comprises a plurality of alternating elongated
depressions 25 and elongated elevations 26, wherein the depressions 25 are formed
each as an elongated concave groove 27, all explained in more detail in accordance
with the FIG. 2 and 3.
[0063] Still referring to FIG. 1 the orientation of the elevations 26 and depressions 25
are substantially perpendicular or possibly angled (e.g. 10°, 20°, 30°, 40°, 50°,
or 60° or any value in between) to a local fluid flow direction of the cooling fluid
24. This should provide sufficient heat transfer to cool the panel 11.
[0064] Now referring to FIG. 2 and 3, the alternating elongated depressions 25 and elongated
elevations 26 are shown in more detail. FIG. 2 and 3 show in more detail a section
V of the combustion liner as identified by an ellipse in FIG. 1. FIG. 2 shows a cross-sectional
view in the same plane as FIG. 1. FIG. 3 shows an angled three-dimensional view of
the same combustion liner section V. In FIG. 3 the drawing plane of FIG. 1 and 2 is
a shown fictitious plane identified by reference numeral 40.
[0065] This fictitious plane 40 and the drawing plane of FIG. 2 is a plane perpendicular
to an expanse of the groove 27 and perpendicular to the first surface 21 of the panel
11.
[0066] According to FIG. 2 a section of the panel 11 is shown, with a substantially flat
first surface 21 and a contoured second surface 22. The second surface 22 shows repetitively
depressions 25 and elevations 26, which extend perpendicular to the drawing plane
to elongated elements. The depressions 25 smoothly merge to the elevations 26. The
form of the depressions 25 and the elevations 26 follow a concave groove 27, which
again is elongated in direction perpendicular to the drawing plane. The elevations
26 itselves are formed as leveled ridges with top surfaces 31. Each ridge has a kink
between a first one of the curved groove 27 and one of the top surfaces 31 and a further
kink from that top surface 31 to a consecutive curved groove 27.
[0067] The groove 27 is concave. According to the shown embodiment the groove 27 even shows
a circular cylindrical shape, i.e. the groove 27 forms a segment of circular cylindrical
recess and the follows the shape of an arc of a circle in the given cross-sectional
view. The radius of this circular cylindrical recess is indicated as radius R, which
is shown as a radius about an axis Y. This axis Y is preferably perpendicular to the
drawing plane and parallel to the elongation of the grooves 27.
[0068] It is the goal that cross flowing cooling fluid (in FIG. 1 identified as cooling
fluid 24) provides heat transfer between the panel 11 and the cooling fluid 24. The
dimensions of the second surface structures can be defined as pitch P between two
elevations 26, the depth D of the groove 27, defined as a maximum depth of one of
the depressions 25 in relation to a maximum height of the ridge 30 of an adjacent
one of the elevations 26; and by a width W which is defined as an average transversal
width - i.e. in the drawing plane - of the levelled top surface 31 of the levelled
ridge 30.
[0069] Preferably, to gain cooling effect via convective cooling, the dimension may be in
the range of:
![](https://data.epo.org/publication-server/image?imagePath=2017/40/DOC/EPNWA1/EP16163258NWA1/imgb0007)
[0070] In the shown example W/D may be 0.8, so showing a substantially narrow ridge. R/D
may be 12, so that about roughly 40° of a cylinder wall is present as a groove. P/D
may also be 12, defining that the grooves are fairly flat. As mentioned before, different
configuration values may also be applicable.
[0071] FIG. 3 explicitly shows the configuration of FIG. 2 and explicitly shows that the
grooves 27, the depressions 25, the elevations 26 are elongated along the second surface
22. FIG. 3 also depicts that the panel 11 may be curved itself.
[0072] The shown design is advantageous as a single milling cutter can be used to create
the shape of a concave groove 27. This simplifies the manufacturing process of surface
machining. The difference lies in the cutting head compared to rectangular turbulators.
In the case of the rectangular turbulators the cutter angle may need to be changed
several times to generate sharp corners whereas in the wave form it is possible to
use a circular cutter which does not need any manual adjustment. It reduces the manufacturing
lead-time as well as labor-tool interaction drastically. In consequence the manufacturing
costs are reduced. Even though manufacturing is simplified, the cooling effect and
the overall gas turbine efficiency remain intact.
[0073] The usage of the milling cutter and the milling tool is shown in FIG. 4 and 5.
[0074] FIG. 4 shows a milling cutter 200 with a circular shape, which will follow a rotational
path so that a segment of the groove 27 is machined at a specific location. Later
the panel 11 and/or the milling cutter 200 will be repositioned to another so that
the milling cutter 200 will create a further segment of the groove 27. The original
material width of the panel 11 is indicated by a dotted line and the reference numeral
201. According to Fig. 4 the machining is performed at groove 27', groove 27" has
already been created, and groove 27"' would be the next groove to be machined.
[0075] The rotational path of the milling cutter 200 may be perpendicular to the expanse
of the groove 27, as implied in all the shown figures. The rotational path of the
milling cutter 200 may also be angled to the groove 27 which would allow grooves that
do not follow the arc of a circle but follow an elliptical path.
[0076] These grooves 27', 27", 27 "', as mentioned in relation to FIG. 4, are also indicated
in FIG. 5. As shown in FIG. 5 the component 10, if - at least in parts - being rotational
symmetric, may be placed on a rotatable platform 210. One groove after another is
machined into a surface of the component 10 via a milling cutter 200, particularly
its cutter head. The cutter head may provide a lateral movement compared to the main
rotation of the rotatable platform 210. The lateral movement will create a segment
of the groove 27', which will be completed by the rotation of the rotatable platform
210.
[0077] According to FIG. 5 already machined surfaces are shown with solid lines. Surfaces
to be machined are identified with dashed lines.
[0078] This machining process may be called lathing.
[0079] As you can see, once the machining process is completely performed, the component
10 and its surface 22 will show a plurality of grooves 27', 27'', 27"', etc. at its
radial outwards surface. The component 10 can then be installed e.g. as an outer wall
102" (see FIG. 1) of a combustion chamber liner. In a similar way an inner wall 102'
can be machined.
[0080] Previously the invention was explained in conjunction with a combustion chamber liner.
Other elements of a gas turbine engine or other types of rotating machine that experience
strong heat can also be equipped with these features. For example in a gas turbine
engine, a transition duct can be equipped with this surface structure. Also heat shields,
for example use in the combustion chamber or at the turbine section of a gas turbine
engine, can be equipped accordingly. Furthermore the invention can be applied for
exhaust nozzles in gas turbines or turbine shrouds. Besides, the invention can also
be used for a casing located in a hot region of an engine. In case of combustion chamber
liners, the corrugated feature can be applied to a surface of the single liner facing
away from the combustion chamber or in case of a double liner (as shown in the figures),
being located in a passage defined by the double liner. In both cases the machined
surface will be facing away from the combustion chamber interior, after it has been
installed.
[0081] Beyond that, other types of machines can use this inventive feature as long as cooling
air may be provided to that component. As a gas turbine engine has a compressor included
into the system in which air is compressed which can be used also as cooling air,
and due to the temperature levels at a gas turbine engine, the invention is specifically
advantageous to be incorporated in a gas turbine engine.
1. Turbomachine component (10) arrangeable in a turbomachine (1), particularly a gas
turbine engine,
the turbomachine component (10) built in parts from a curved or planar panel (11),
the panel (11) comprising a first surface (21) and a second surface (22),
wherein the turbomachine component (10) is arrangeable such that, during operation
of the turbomachine (1), the first surface (21) is affected by thermal radiation (23)
and the second surface (22) is affected by a cooling fluid (24) travelling along the
second surface (22),
wherein the second surface (22) comprises a plurality of alternating elongated depressions
(25) and elongated elevations (26), wherein the depressions (25) are formed each as
an elongated concave groove (27).
2. Turbomachine component (10) according to claim 1,
characterised in that
the concave groove (27) follows in cross-section a shape of a part of an arc of a
circle when the cross-section is taken from a direction perpendicular to ridges (29)
of one of the elevations (26).
3. Turbomachine component (10) according to claims 1 or 2,
characterised in that
in case the panel (11) is planar, the concave groove (27) forms a segment of circular
cylindrical recess, and/or
in case the panel (11) is curved, the concave groove (27) forms a segment of skewed
circular cylindrical recess following a contour of the panel (11).
4. Turbomachine component (10) according to claim XY,
characterised in that
the depressions (25) are manufactured by machining the depressions (25) into the second
surface (22).
5. Turbomachine component (10) according to claim XY,
characterised in that
the depressions (25) are manufactured by machining the depressions (25) into the second
surface (22) via a milling cutter, wherein one of the milling cutter and the second
surface (22) follows a rotation along a circular arc section (28).
6. Turbomachine component (10) according to claim XY,
characterised in that
ridges (29) of the elevations (26) are arranged angled to a flow direction of the
cooling fluid (24) along the second surface (22) during operation of the turbomachine
(1), wherein an angle of attack of the cooling fluid (24) onto the ridges (29) is
between -60° and +60° in respect of a direction perpendicular to the ridges (29).
7. Turbomachine component (10) according to claim XY,
characterised in that
the elevations (26) are each formed as a levelled ridge (30).
8. Turbomachine component (10) according to claim XY,
characterised in that
a width W is defined as an average transversal width of a levelled top surface (31)
of the levelled ridge (30), and
a depth D is defined as a maximum depth of one of the depressions (25) in relation
to a maximum height of the ridge (30) of an adjacent one of the elevations (26),
wherein the depressions (25) and elevations (26) are configured such that W/D is in
the range of
![](https://data.epo.org/publication-server/image?imagePath=2017/40/DOC/EPNWA1/EP16163258NWA1/imgb0008)
preferably
9. Turbomachine component (10) according to claim XY,
characterised in that
the depressions (25) and the elevations (26) are sized and oriented to act as turbulators
for the cooling fluid (24) during operation of the turbomachine (1).
10. Turbomachine component (10) according to claim XY,
characterised in that
a radius R is defined for a radius of the concave groove (27), with the radius taken
in a plane (40) perpendicular to an expanse of the groove (27) and perpendicular to
the first surface (21) of the panel (11), and
a depth D is defined as a maximum depth of one of the depressions (25) in relation
to a maximum height of the ridge (30) of an adjacent one of the elevations (26),
wherein the depressions (25) and elevations (26) are configured such that R/D is in
the range of
![](https://data.epo.org/publication-server/image?imagePath=2017/40/DOC/EPNWA1/EP16163258NWA1/imgb0010)
preferably
11. Turbomachine component (10) according to claim XY,
characterised in that
a pitch P is defined for a shortest transversal distance between two adjacent elevations
(26) of the elevations (26), and
a depth D is defined as a maximum depth of one of the depressions (25) in relation
to a maximum height of the ridge (30) of an adjacent one of the elevations (26),
wherein the depressions (25) and elevations (26) are configured such that P/D is in
the range of
![](https://data.epo.org/publication-server/image?imagePath=2017/40/DOC/EPNWA1/EP16163258NWA1/imgb0012)
preferably
12. Manufacturing method of a turbomachine component (10), particularly a gas turbine
engine component for usage in a combustor or an expansion turbine of a gas turbine
engine, comprising the steps of:
a) providing a milling machine with a milling cutter (200); and
b) providing to the milling machine a turbomachine component (10) comprising a panel
(11), the panel (11) comprising a substantially flat first surface (21) and a substantially
flat second surface (22); and
c) cutting into the second surface (22) of the panel (11) a section of a depression
(25) by rotating the milling cutter (200) and/or the turbomachine component (10) relative
to another such that the milling cutter (200) machines a segment of a concave groove
(27), particularly a segment of a circular cylindrical groove, into the second surface
(22).
13. Manufacturing method of a turbomachine component (10) according to claim 12,
characterized in that
the relative rotating in step c) comprises a step of rotating the milling cutter (200)
about an axis of rotation (Y).
14. Manufacturing method of a turbomachine component (10) according to claims 12 or 13,
comprising the further step of:
d) repositioning of the panel (11) in reference to the milling machine laterally to
a plane of rotation of the milling cutter (200); and
f) further execution of step c) so that a previously cut section of the depression
is extended by a further cut section into the second surface (22); and
g) plural repetition of consecutively executed steps d) and f);
wherein an elongated first depression (27) is machined.
15. Manufacturing method of a turbomachine component (10) according to claim 14,
comprising the further step of:
h) repositioning of the panel (11) in reference to the milling machine lateral to
a milling path as defined by steps c) to g) and parallel to the second surface (22);
and
i) performing steps c) to g) for cutting an elongated further depression (27') into
the second surface (22) parallel to the elongated first depression (27).