U.S. patent application number 12/748382 was filed with the patent office on 2010-07-22 for engine wall structure and a method of producing an engine wall structure.
This patent application is currently assigned to Volvo Aero Corporation. Invention is credited to Arne Boman.
Application Number | 20100180575 12/748382 |
Document ID | / |
Family ID | 37836088 |
Filed Date | 2010-07-22 |
United States Patent
Application |
20100180575 |
Kind Code |
A1 |
Boman; Arne |
July 22, 2010 |
ENGINE WALL STRUCTURE AND A METHOD OF PRODUCING AN ENGINE WALL
STRUCTURE
Abstract
An engine wall structure includes an inner wall to which hot gas
is admitted during engine operation, an outer wall, which is colder
than the inner wall during engine operation, and at least two webs
that connect the inner wall with the outer wall and delimit a
cooling duct between the walls. The webs are mainly formed by a
first material and the inner wall is mainly formed by a second
material of other composition and other heat conductivity than the
first material.
Inventors: |
Boman; Arne; (Trollhattan,
SE) |
Correspondence
Address: |
WRB-IP LLP
801 N. Pitt Street, Suite 123
ALEXANDRIA
VA
22314
US
|
Assignee: |
Volvo Aero Corporation
Trollhattan
SE
|
Family ID: |
37836088 |
Appl. No.: |
12/748382 |
Filed: |
March 27, 2010 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
12063826 |
Feb 14, 2008 |
|
|
|
PCT/SE2005/001293 |
Sep 6, 2005 |
|
|
|
12748382 |
|
|
|
|
Current U.S.
Class: |
60/266 |
Current CPC
Class: |
Y10T 29/49346 20150115;
F05D 2300/5024 20130101; F05D 2230/642 20130101; F05D 2230/60
20130101; F02K 9/64 20130101; F02K 9/972 20130101 |
Class at
Publication: |
60/266 |
International
Class: |
F02K 9/64 20060101
F02K009/64; F02K 9/97 20060101 F02K009/97 |
Claims
1-15. (canceled)
16. An engine wall structure that comprises an inner wall, to which
hot gas is admitted during engine operation, an outer wall, which
is colder than the inner wall during engine operation, and at least
two webs that connect the inner wall with the outer wall and
delimit a cooling duct between the walls, wherein the webs are
mainly comprised by a first material and that the inner wall is
mainly comprised by a second material of other composition and
other heat conductivity than the first material.
17. An engine wall structure according to claim 16, wherein the
composition of the material of the webs is substantially equal to
the composition of the material of the outer wall.
18. An engine wall structure according to claim 16, wherein the
material of the inner wall has higher heat conductivity than the
material used for the webs.
19. An engine wall structure according to claim 16, wherein the
inner wall comprises a copper or a copper-based alloy, and that the
webs comprises steel.
20. An engine wall structure according to claim 16, wherein the
material of the inner wall has a higher temperature resistance than
the material of the webs.
21. An engine wall structure according to claim 16, wherein the
material of the webs has higher heat conductivity than the material
of the inner wall.
22. An engine wall structure according to claim 21, wherein the
inner wall comprises steel and that the webs comprises aluminum or
an aluminum-based alloy.
23. An engine wall structure according to claim 16, wherein the
material of the outer wall and the material of the webs have
corresponding heat conductivity properties.
24. An engine wall structure according to claim 16, wherein the
material of the outer wall and the material of the webs have
corresponding properties as to their mechanical strength.
25. An engine wall structure according to claim 16, wherein the
engine wall structure defines a thrust nozzle wall of a rocket
engine.
26. An engine wall structure according to claim 16, wherein the
first material is deposited onto the inner wall by
electro-deposition.
Description
[0001] The present application is a divisional of U.S. application
Ser. No. 12/063,826, filed Feb. 14, 2008.
BACKGROUND AND SUMMARY
[0002] The present invention relates to an engine wall structure
and to a method of producing an engine wall structure that
comprises an inner wall, to which hot gas is admitted during engine
operation, an outer wall, which is colder than the inner wall
during engine operation, and at least two webs that connect the
inner wall with the outer wall and delimit a cooling duct between
said walls.
[0003] During engine operation, any cooling medium may flow through
the ducts. However, in particular, the invention relates to engine
wall structures and a process for manufacturing engine wall
structures in which there is a plurality of such webs dividing the
space between the walls into a plurality of ducts, in particular
for cooling the firing chamber walls and the thrust nozzle walls of
rocket engines driven with hydrogen as a fuel or a hydrocarbon,
i.e. kerosene, wherein the fuel is introduced in the cold state
into the wall structure, is delivered through the cooling ducts
while absorbing heat via the inner wall, and is subsequently used
to generate the thrust. Heat is transferred from the hot gases to
the inner wall, further on to the fuel, from the fuel to the outer
wall, and, finally, from the outer wall to any medium surrounding
it. Heat is also transported away by the coolant media as the
coolant temperature increases by the cooling. The hot gases may
comprise a flame generated by combustion of gases and/or fuel.
[0004] Accordingly, the engine wall structure is preferably a
thrust nozzle wall, preferably of a rocket engine.
[0005] According to prior art, the engine wall structures of
regeneratively cooled combustion chambers for liquid propellant
rocket engines, cooling channels or ducts are machined, for example
by milling, in a sheet or core that will form the inner wall, or at
least part of an inner wall. In the case of regenerative cooling,
this inner wall sheet may mainly comprise copper or a copper alloy.
However, other materials such as steel may also be used as the
core. The resulting ducts are delimited by remaining webs, and may
subsequently be filled with a filler material such as a conductive
resin.
[0006] Subsequently, an outer cover, defining the outer wall, is
applied to and attached to the projecting webs, for example by
means of electro-deposition. The outer wall may comprise plural
layers of a material such as nickel or a nickel-alloy. The outer
cover may, possibly, also be attached to the inside of the inner
wall sheet, thereby fully surrounding the core. The filler
material, transformed by means of heating into a liquid state, is
then drained off through an end of the respective duct.
[0007] However, prior art results in an insufficient control of the
exact thickness of the remaining inner wall, due to the inherent
problem of obtaining an exact milling depth in the inner wall
sheet. As a result, the control of the heat transfer becomes less
predictable than it would have been if the exact inner wall
thickness had been known. Also the area of the cross section of the
ducts depends of the milling depth. Since alterations of that area
will result in correspondingly altered flow conditions in the duct,
this will also affect the effective heat transfer and the
possibility of predicting the latter.
[0008] Moreover, the requirements on the thermal conductivity of
the inner wall and the webs may differ substantially. By
regenerative cooling of an engine wall structure, by which the
cooling medium has a high heat absorption capacity by the large
coolant mass flow and largely comprises fuel to be used in a
subsequent combustion process, the conductivity of the inner wall
is much more decisive for the outcome of the cooling than is the
conductivity of the webs. By so called dump cooling, by which the
cooling medium has a low heat absorption capacity by a low coolant
mass flow, the heat conductivity of the webs may be more decisive
for the outcome of the cooling than will the conductivity of the
inner wall. This insight has not been mentioned at all by prior
art.
[0009] It is desirable to provide an engine wall structure and a
method of producing an engine wall structure as initially defined,
by which heat is effectively and predictably transferred from the
inner wall to the outer wall through a cooling medium, preferably a
fuel, in one or more ducts and through the material of the webs
that delimit said duct or ducts and that connect the inner and
outer walls.
[0010] The invention shall also present an engine wall structure
the construction of which is such that it promotes the obtaining of
a very precisely controlled inner wall thickness upon generation of
the webs as well as a facilitated subsequent attachment of the
outer wall to the webs, especially when the inner wall material is
different from the outer wall material and not easily connected by
any metal fusion process. The design of the engine wall structure
should also be such that it takes into consideration the different
heat conductivity requirements of the inner wall and the webs.
[0011] According to an aspect of the present invention, the webs
are formed by application of a first material onto the inner wall,
said inner wall being comprised by a second material of other
composition and other heat conductivity than said first
material.
[0012] Any suitable technique for applying the webs to the inner
wall may be used, such as welding of solid pieces of the first
material onto the inner wall. However, deposition of the first
material, preferably electro-deposition, is preferred.
[0013] By building the webs by means of application thereof onto
the inner wall, preferably by deposition and most preferably by
means of electro-deposition, the thickness of that wall will not be
affected like when the webs are produced through machining of the
inner wall, while, at the same time, the height of the web can be
very finely adjusted, for example by means of a final milling of
the web top. By using materials of different composition and heat
conductivity, the webs may be tailored for their individual,
specific functions, especially regarding the conductivity.
Subsequent to the formation of the webs, the outer wall is attached
to the webs.
[0014] Preferably, a removable mask is placed onto said inner wall
before the deposition of the webs is begun, said mask defining
spaces in which the webs are deposited onto the inner wall.
Thereby, a precise deposition of the web material is promoted.
[0015] According to a preferred embodiment the outer wall is
connected to the webs by means of a metal fusion operation,
preferably welding, and most preferably laser welding. Accordingly,
the outer wall comprises a sheet or the like that is connected to
the webs.
[0016] Preferably, the composition of the material of the webs is
substantially equal to the composition of the material of the outer
wall. Thereby, any metal fusion process for attaching the second
wall to the webs is facilitated.
[0017] Preferably, the material of the inner wall has higher heat
conductivity than the material used for the webs. This is typically
an advantage in those cases when there is a regenerative cooling
with a high coolant flow rate or when the cooling medium has a high
density, such as when in liquid state, resulting in a high heat
absorption, but still a relatively low temperature of the cooling
medium and, accordingly, in a relatively low temperature of the
webs and the outer wall. The heat conductivity of the material of
the inner wall will be decisive for the amount of heat that will be
transferred to the cooling medium. The webs and the outer wall may
then, preferably, be made of a material of higher mechanical
strength than the material of the inner wall, while their
conductivity is of less importance. Preferably, regenerative
cooling is applied to stage combustion cycle rocket engine nozzles
or expander cycle rocket engine nozzles.
[0018] In a preferred embodiment, with rapidly flowing cooling
medium or a cooling medium of high density, preferably liquid fuel,
the inner wall comprises a copper or a copper-based alloy, and the
webs comprise steel. Typically, this is preferred for a so-called
regenerative cooling when hydrogen or kerosene to be used as fuel
is also used as the cooling medium. The flow of the cooling medium
should be such that a temperature well below the melting point of
copper or copper alloy is obtained in the inner wall, preferably
below 800 K. The use of a material with a remarkably lower heat
conductivity, such as steel, for the inner wall, would result in a
build up of a too high temperature in the inner wall and, as a
result, a deterioration of the inner wall material.
[0019] Several materials, such as steel, used for inner walls and
webs have relatively low heat conductivity at low temperatures. A
low temperature of the cooling medium, for instance at the cooling
duct inlet, will result in a low temperature of the engine wall
webs, and a low heat conductivity thereof. Also, if the heat
transferability of the cooling medium is poor, for example due to a
low flow rate or due to a low cooling medium density, it would be
desired to compensate this by the use of a highly heat conductive
material, such as aluminum, for the webs, and possibly also for the
outer wall. Therefore, according to one aspect of the invention,
the material of the webs has higher heat conductivity than the
material of the inner wall. This feature is preferred for so called
dump cooling. Preferably, dump cooling is applied to gas generator
cycle rocket engine nozzles.
[0020] If the cooling ability of the engine wall structure,
including the cooling medium, is poor due to a low cooling medium
flow rate or a low cooling medium density, the temperature of the
inner wall might be to high for permitting the use of a highly
heat-conducting material such as aluminum for the inner wall. In
such cases it is preferred that the temperature resistance of the
material of the inner wall is better than that of the web material.
Thus, according to a preferred embodiment of the invention, the
inner wall comprises steel or copper and the webs comprise aluminum
or an aluminum-based alloy.
[0021] According to another aspect of the present invention, an
engine wall structure comprises an inner wall, to which hot gas is
admitted during engine operation, an outer wall, which is colder
than the inner wall during engine operation, and at least two webs
that connect the inner wall with the outer wall and delimit a
cooling duct between said walls, characterised in that the webs are
mainly comprised by a first material and that the inner wall is
mainly comprised by a second material of other composition and
other heat conductivity than said first material. Preferred
embodiments of the engine wall structure of the invention include
those embodiments that have been described above with regard to the
inventive method, especially with regard to the specific
compositions of the first and second materials.
BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Preferred embodiments of the present invention will now be
described by way of example, with reference to the annexed
drawings, on which:
[0023] FIG. 1 shows a cross section of a nozzle provided with an
engine wall structure according to the invention.
[0024] FIG. 2 is an enlargement of a segment of the engine wall
structure according to FIG. 1
[0025] FIG. 3 is a cross section of an engine wall structure
according to a first embodiment of the invention,
[0026] FIG. 4 is a cross section of an engine wall structure
according to a second embodiment of the invention, and
[0027] FIG. 5 is a cross section of a part of the engine wall
structure during the manufacture thereof.
DETAILED DESCRIPTION
[0028] FIGS. 1 and 2 are schematic representations of the thrust
nozzle 1 of a rocket engine. The nozzle 1 comprises and is defined
by a cone-shaped or bell-shaped engine wall structure 2. The engine
wall structure 2 is provided with an inner wall 3 and an outer wall
4, interconnected by a plurality of webs 5, as shown in FIGS. 3 and
4. In the space between the inner wall 3 and the outer wall 4 there
are ducts 6 that are used for cooling purposes. During operation of
the engine a cooling medium, preferably the fuel or part of the
fuel of the engine, is permitted to flow through the ducts 6 for
the purpose of cooling the engine wall structure 2. This technique
applies to satellite launchers and space planes, and also in
satellite thrusters, nuclear reactors and high efficiency boilers,
and it can also be applied to heat shields or to the nose cones of
vehicles travelling at very high speed. When a fuel, preferably in
a liquid state, is used as the cooling medium, the technique is
called regenerative cooling. Then, the heat absorption of the
cooling medium is relatively high, since a large mass of fuel is
permitted to flow through the engine wall ducts 6.
[0029] When the cooling medium comprises a gas or gas mixture that
is not further used for any particular purpose, but only used for
cooling purposes and then exited into the atmosphere, the technique
is called dump cooling. Then, the heat absorption of the cooling
medium is relatively low. Typically, dump cooling is applied when
the flame of the engine generates a relatively low heat load.
[0030] The inner wall 3 and the outer wall 4 are mainly constituted
by metals, preferably different metals of different heat
conductivity and different mechanical strength, since the
requirements on such properties will differ for the inner and outer
walls 3, 4. The webs 5 are also made of metal.
[0031] The cooling ducts 6 are divided by the webs 5 and extend in
the longitudinal direction of the nozzle 1, i.e. in the hot gas
flow direction, as seen in particular in FIG. 2. The nozzle is
cone-shaped, whereby the width of the ducts 6 increase towards the
wider end of the nozzle 1, and the thickness of the webs 5 is
generally constant throughout the length of the nozzle 1.
[0032] FIG. 3 shows a first embodiment of the invention in which
the inner wall 3 is mainly constituted by a material of different
composition and different heat conductivity than the material of
the webs 5 directly connected thereto. The webs 5 have been
attached to the inner wall 3 by means of a metal deposition method,
preferably electro-deposition. The deposition or build up of the
webs is schematically represented in FIG. 5, in which there is
shown a mask 7 that is placed on top of the inner wall 3 before the
application of the webs. The mask 7 has a height or thickness in a
direction normal to the surface of the inner wall 3 that
corresponds to or even exceeds that desired height of the webs 5.
The mask 7 leaves open channels 8 into which the web material is
brought for the purpose of being deposited on the inner wall 3.
Once the deposition of the web material has been ended, the mask 7
is removed from the surface of the inner wall 3.
[0033] The mask 7 may be tailored in accordance with different
pre-conditions, thereby greatly facilitating the application of
different web geometries. FIG. 4 shows an embodiment in which the
mask 7 has been given such a shape that the resulting webs 5 get
wider towards
[0034] the outer wall 4. This specific geometry might be used in
order to diminish the cross section area of the ducts 6 in order to
enforce a more rapid flow rate of the cooling medium and, thereby,
a more effective cooling. This effect is also achieved thanks to
the interface area between the webs and the outer wall 4 becoming
larger than would otherwise be the case.
[0035] Once the deposition of the web material has been completed,
the height of the webs 5 is finely adjusted, for example by means
of milling, in order to establish a very precise web height, and,
possibly, also the web width. Preferably, but not necessarily, this
operation is performed after removal of the mask 7. Thereafter, the
outer wall 4, constituted by a sheet of material, is positioned on
top of the webs 5 and attached thereto, preferably by means of any
metal fusion operation, such as laser welding.
[0036] As already told, the web material differs from the inner
wall material, in particular regarding its heat conductivity, and
possibly also with regard to its mechanical strength and
temperature resistance.
[0037] The outer wall material and the web material should be
easily interconnected by means of any metal fusion process. This is
most easily achieved if their compositions are substantially equal.
Accordingly, the outer wall material and the web material may have
corresponding heat conductivity properties as well as mechanical
properties.
[0038] For applications with a high cooling effect of the cooling
medium, for example when the flow rate of the latter is high and/or
when the density thereof is high, as for a liquid cooling medium,
the heat conductivity of the inner wall 3 will be crucial to the
total heat transfer.
[0039] Then, a high conductivity material such as copper is
preferred as the inner wall material. The web material as well as
the outer wall material should, of course, also have a certain
conductivity, but since a large part of the heat is absorbed and
carried away by the cooling medium, it might be substantially lower
than that of the inner wall 3. Therefore, a material of higher
mechanical strength could be used as web material and outer wall
material. In a preferred embodiment steel is preferred as web and
outer wall material.
[0040] For applications with a low cooling effect of the cooling
medium, for example when the flow rate of the latter is low or when
the density thereof is low, as for a gaseous cooling medium, the
heat conductivity of the webs becomes increasingly important in
order to let a larger part of the heat be transferred from the
inner wall 3 to the outer wall 4 through the webs. It is then
preferred that the heat conductivity of the web material is higher
than that of the inner wall material. According to a preferred
embodiment, the inner wall material mainly comprises steel, while
the web material mainly comprises aluminum or an aluminum alloy.
This is a preferred embodiment in cases when the cooling medium in
the ducts 6 has a relatively low temperature, thereby permitting
steel to be used as the inner wall material, and when the cooling
medium is in gaseous state with inherently poor heat absorption
capacity.
[0041] It should be realised that the above description of the
invention only has been made by way of example and that, of course,
a person skilled in the art will recognise a plurality of
alternative embodiments, all however within the scope of the
invention as defined in the annexed patent claims, supported by the
description and the drawings.
* * * * *