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Sommaire du brevet 2643956 

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Disponibilité de l'Abrégé et des Revendications

L'apparition de différences dans le texte et l'image des Revendications et de l'Abrégé dépend du moment auquel le document est publié. Les textes des Revendications et de l'Abrégé sont affichés :

  • lorsque la demande peut être examinée par le public;
  • lorsque le brevet est émis (délivrance).
(12) Demande de brevet: (11) CA 2643956
(54) Titre français: CARTERS DE TRANSITION SPIRALES POUR ENSEMBLES DE TURBINE
(54) Titre anglais: TRANSITION SCROLLS FOR USE IN TURBINE ENGINE ASSEMBLIES
Statut: Réputée abandonnée et au-delà du délai pour le rétablissement - en attente de la réponse à l’avis de communication rejetée
Données bibliographiques
(51) Classification internationale des brevets (CIB):
  • F23R 3/42 (2006.01)
  • F02C 3/14 (2006.01)
  • F02C 7/12 (2006.01)
(72) Inventeurs :
  • SCHUMACHER, JURGEN C. (Etats-Unis d'Amérique)
  • CRITCHLEY, IAN L. (Etats-Unis d'Amérique)
  • WALHOOD, DAVID G. (Etats-Unis d'Amérique)
  • KUJALA, STONY W. (Etats-Unis d'Amérique)
  • WOODCOCK, GREGORY O. (Etats-Unis d'Amérique)
(73) Titulaires :
  • HONEYWELL INTERNATIONAL INC.
(71) Demandeurs :
  • HONEYWELL INTERNATIONAL INC. (Etats-Unis d'Amérique)
(74) Agent: GOWLING WLG (CANADA) LLPGOWLING WLG (CANADA) LLP
(74) Co-agent:
(45) Délivré:
(22) Date de dépôt: 2008-11-17
(41) Mise à la disponibilité du public: 2009-07-18
Licence disponible: S.O.
Cédé au domaine public: S.O.
(25) Langue des documents déposés: Anglais

Traité de coopération en matière de brevets (PCT): Non

(30) Données de priorité de la demande:
Numéro de la demande Pays / territoire Date
12/061,360 (Etats-Unis d'Amérique) 2008-01-18

Abrégés

Abrégé anglais


An engine assembly includes a combustor having a combustion chamber
in which an air and fuel mixture is combusted to produce combustion gases. The
engine assembly further includes a transition scroll coupled to the combustor
for
receiving the combustion gases. The transition scroll includes an interior
surface,
an exterior surface, and effusion cooling holes for providing cooling air to
the
interior surface. The engine assembly further includes a turbine coupled to
the
transition scroll for receiving and extracting energy from the combustion
gases.

Revendications

Note : Les revendications sont présentées dans la langue officielle dans laquelle elles ont été soumises.


CLAIMS
What is claimed is:
1. An engine assembly, comprising:
a combustor comprising a combustion chamber in which an air and fuel
mixture is combusted to produce combustion gases;
a transition scroll coupled to the combustor for receiving the combustion
gases, the transition scroll comprising an interior surface, an exterior
surface, and
effusion cooling holes for providing cooling air to the interior surface; and
a turbine coupled to the transition scroll for receiving and extracting
energy from the combustion gases.
2. The engine assembly of claim 1, wherein the transition scroll is
helical with an inlet and a B-width outlet.
3. The engine assembly of claim 2, wherein at least a portion of the
effusion cooling holes are adjacent to the inlet.
4. The engine assembly of claim 2, wherein the transition scroll has
an inner portion and an outer portion, the effusion cooling holes comprising a
first
group with a first density on the outer portion and a second group with a
second
density on the inner portion, the first density being greater than the second
density.
5. The engine assembly of claim 1, wherein the transition scroll has a
non-circular cross-section.
6. The engine assembly of claim 1, wherein the transition scroll
comprises an inlet and a main body coupled to the inlet, the effusion cooling
holes
being formed on the inlet.
11

7. The engine assembly of claim 6, wherein the effusion cooling holes
are additionally formed on the main body.
8. The engine assembly of claim 7, wherein the effusion cooling holes
on the inlet have a greater density than the effusion cooling holes on the
main
body.
9. The engine assembly of claim 7, wherein the main body has a
helical configuration with an inner section and an outer section, the effusion
cooling holes on the main body comprising a first group with a first density
on the
outer section and a second group with a second density on the inner section,
the
first density being greater than the second density.
10. The engine assembly of claim 7, wherein main body comprises a
first wall coupled to a second wall.
11. The engine assembly of claim 10, wherein the first wall and second
wall each have a first portion and a seam portion at which the first and
second
walls are coupled together, and the effusion cooling holes being oriented at a
first
angle in the first portions and at a second angle in the seam portions, the
second
angle being larger than the first angle.
12. The engine assembly of claim 1, wherein the effusion cooling holes
comprise a first group with a first density and a second group with a second
density.
13. The engine assembly of claim 1, wherein the effusion cooling holes
are unevenly spaced.
12

14. A transition scroll for receiving combustion gases from a
combustor and providing the combustion gases to a turbine, the transition
scroll
comprising:
a body configured to extend between the combustor and the turbine scroll,
the body having a hot surface and a cold surface during operation; and
effusion cooling holes formed in the body for supplying cooling air to the
hot surface.
15. The transition scroll of claim 14, wherein the body is helical with
an inlet and a B-width outlet, at least a portion of the effusion holes being
adjacent
the inlet.
16. The transition scroll of claim 15, wherein the body has an inner
portion and an outer portion, the effusion cooling holes comprising a first
group
with a first density on the outer portion and a second group with a second
density
on the inner portion, the first density being greater than the second density.
17. The transition scroll of claim 14, wherein the body has a non-
circular cross-section.
18. The transition scroll of claim 14, wherein the effusion cooling
holes comprise a first group with a first density and a second group with a
second
density.
19. The transition scroll of claim 14, wherein the effusion cooling
holes are unevenly spaced.
20. An engine assembly, comprising:
a can combustor comprising a combustion chamber in which an air and
fuel mixture is combusted to produce combustion gases;
13

a turbine for receiving and extracting energy from the combustion gases;
and
a transition scroll coupling the can combustor to the turbine, the transition
scroll being helical with an inlet coupled to the can combustor and a B-width
outlet coupled to the turbine, the transition scroll having a hot surface, a
cold
surface, and effusion cooling holes for providing a layer of cooling air to
the hot
side, the transition scroll further having an inner portion and an outer
portion, the
effusion cooling holes comprising a first group with a first density on the
outer
portion and a second group with a second density on the inner portion, the
first
density being greater than the second density.
14

Description

Note : Les descriptions sont présentées dans la langue officielle dans laquelle elles ont été soumises.


- ------ - - ---~- - -CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
TRANSITION SCROLLS FOR USE IN TURBINE ENGINE ASSEMBLIES
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR
DEVELOPMENT
[0001] This invention was made with Government support under contract
number N00019-02-C-3002 awarded by the JSF-PTMS program of the US
Government. The Government has certain rights in this invention.
TECHNICAL FIELD
[0002] The present invention generally relates to turbine engine assemblies
and
more specifically, to transition scrolls for use in turbine engines
assemblies.
BACKGROUND
[0003] Gas turbine engines are used to power aircraft or various other types
of
vehicles and systems. Engines typically include a compressor that receives and
compresses an incoming gas such as air. A combustor receives the compressed
gas, mixes it with fuel, and ignites the mixture to produce a high-pressure,
high-
velocity exhaust gas. A transition scroll receives, redirects, and provides
the
exhaust gas to a turbine that extracts energy for the engine. The transition
scroll is
a hollow, generally coiled component that receives a tangential flow of the
hot
combustion gases into its interior and exhausts these gases through an annular
outlet into the turbine.
1

02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
[0004] The hot combustion gases create a temperature environment that may
limit the useful operating time, and ultimately, the component life of the
engine
assembly. Particularly, the transition scroll can be sensitive to variations
and
extremes in temperature resulting from the combustor exhaust gases. This
consideration is complicated by the helical, asymmetrical nature of the
transition
scroll and the non-uniform temperatures of the exhaust gases exiting from the
combustor. Conventional systems and methods for cooling the transition scroll,
such as louvers and impingement cooling, have met with mixed success at best.
[0005] Accordingly, it is desirable to provide improved systems and methods
for cooling the transition scroll. Furthermore, other desirable features and
characteristics of the present invention will become apparent from the
subsequent
detailed description of the invention and the appended claims, taken in
conjunction with the accompanying drawings and this background of the
invention.
BRIEF SUMMARY
[0006] In one exemplary embodiment, an engine assembly includes a combustor
having a combustion chamber in which an air and fuel mixture is combusted to
produce combustion gases. The engine assembly further includes a transition
scroll coupled to the combustor for receiving the combustion gases. The
transition scroll includes an interior surface, an exterior surface, and
effusion
cooling holes for providing cooling air to the interior surface. The engine
assembly further includes a turbine coupled to the transition scroll for
receiving
and extracting energy from the combustion gases.
[0007] In another exemplary embodiment, a transition scroll is configured to
receive combustion gases from a combustor and provide the combustion gases to
a
turbine. The transition scroll includes a body configured to extend between
the
2

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ATTORNEY DOCKET NO. H0016145
combustor and the turbine scroll. The body has a hot surface and a cold
surface
during operation. The transition scroll includes effusion cooling holes formed
in
the body for supplying cooling air to the hot surface.
[0008] In accordance with yet another exemplary embodiment, an engine
assembly includes a can combustor having a combustion chamber in which an air
and fuel mixture is combusted to produce combustion gases. The engine
assembly further includes a turbine for receiving and extracting energy from
the
combustion gases. The engine assembly further includes a transition scroll
coupling the can combustor to the turbine. The transition scroll is helical
with an
inlet coupled to the can combustor and a B-width outlet coupled to the
turbine.
The transition scroll has a hot surface, a cold surface, and effusion cooling
holes
for providing a layer of cooling air to the hot side. The transition scroll
further
includes an inner portion and an outer portion, and the effusion cooling holes
include a first group with a first density on the outer portion and a second
group
with a second density on the inner portion. The first density is greater than
the
second density.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] The present invention will hereinafter be described in conjunction with
the following drawing figures, wherein like numerals denote like elements, and
wherein:
[0010] FIG. I is a cross-sectional view of a turbine engine assembly in
accordance with an exemplary embodiment;
[0011] FIG. 2 is an isometric view from a first side of an exemplary
transition
scroll of the turbine engine assembly of FIG. 1; and
3

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ATTORNEY DOCKET NO. H0016145
[0012] FIG. 3 is a more detailed view from a second side of the transition
scroll
of FIG. 1.
DETAILED DESCRIPTION
[0013] The following detailed description is merely exemplary in nature and is
not intended to limit the application and uses of exemplary embodiments.
Furthermore, there is no intention to be bound by any theory presented in the
preceding background or the following detailed description.
[0014] Broadly, the exemplary embodiments discussed herein provide cooling
schemes for transition scrolls in engine assemblies. More particularly, the
transition scrolls are provided with effusion cooling holes for supplying a
film of
cooling air to an inner surface. The effusion cooling holes can be positioned
on
and adjacent to an inlet of the transition scroll that receives the exhaust
gases from
the combustor. Moreover, the effusion cooling holes can be used to cool the
relatively large surface area of the turbine scroll in an efficient manner.
Embodiments discussed herein may find beneficial use in many industries and
applications, including aerospace, automotive, and electricity generation, but
particularly in high performance aircraft.
[0015] FIG. 1 is a cross-sectional view of an engine assembly 10 in accordance
with an exemplary embodiment. The engine assembly 10 includes a combustor
12, a turbine 22, and a transition scroll 14 that couples the combustor 12 to
the
turbine 22. The combustor 12 forms a combustion chamber 13 in which
compressed air from a compressor 23 and fuel from a fuel injector 24 are
received
and mixed. The resulting fuel-air mixture is ignited by an igniter 25 to
produce
high energy combustion gases. As will be discussed in further detail below,
the
combustion gases exit the combustor 12 into the transition scroll 14. The
4

.. _ _-_. _ . , -- _ ~ .CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
transition scroll 14 then provides the combustion gases to the turbine 22 for
energy extraction.
[0016] The transition scroll 14 particularly serves to redirect the combustion
gases into an appropriate condition for receipt by the turbine 22. A
combustion
exhaust product discharge area, also known as a B-width 16, couples the
transition
scroll 14 to the turbine 22. Accordingly, the transition scroll 14 distributes
the
combustor gases from a simple cylindrical flow channel to a radially inward
flow
channel between parallel plates, or in an alternate embodiment, an annular
axial
flow channel.
[0017] In many engines, the transition scroll 14 is shaped to be housed within
a
combustor housing 20 with the combustor 12. As such, in addition to being
configured to condition the combusted exhaust gases for the turbine 22, the
transition scroll 14 can be designed to minimize the space taken up within the
limited combustor housing 20 to enable the volume of the combustor 12 to be
optimized. As discussed below in greater detail, the transition scroll 14 may
have
a helical, asymmetrical shape with irregular cross-sections based on
functional as
well as size constraints.
[0018] In one embodiment, the helical design of transition scroll 14 forms an
axial shift region 18, which is a region of transition scroll 14 that is
shifted along
the axis about which the scroll spirals. The axial shift region 18 causes the
cross-
sectional area centroid of a portion of transition scroll 14 to pass beyond B-
width
16. The axial shift region 18 may be useful to provide for additional scroll
volume and to optimize combustor volume.
[0019] FIG. 2 is an isometric view of the transition scroll 14 of the engine
assembly 10 of FIG. 1, and FIG. 3 is a partial isometric view of the
transition
scroll 14 from a different perspective. As discussed above, the transition
scroll 14
is configured to receive combustion exhaust gases, and transition the gases to
be
received by the turbine 22 (FIG. 1). The transition scroll 14 has an inlet 102
with

------ - ------- - -,CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
an inlet flange 104 that is configured to be coupled to the combustor 12 (FIG.
1).
Each component of the transition scroll 14 can be considered to have a hot
side
(e.g., hot side 130 of the inlet 102) that contacts the exhaust gas and a cold
side
(e.g., cold side 132 of the inlet 102) opposite the hot side. In one
embodiment, a
thermal barrier coating can be provided on the hot side of one or more
components of the transition scroll 14. Generally, the inlet 102 is bell-
shaped
with a gradual reduction in cross-sectional area. The inlet 102 transitions
into a
main body 106 that continues the gradual reduction in cross-sectional area. In
various embodiments, the main body 106 is manufactured from a top main body
wall 108, a bottom main body wall 110, and an inner main body wall 112. The
main body 106 is coupled to an end portion 114, which may include a top end
portion wall 116 and a bottom end portion wall 118. The main body 106 and end
portion 114 each at least partially define the B-width 16 that serves as the
outlet
for the transition scroll 14.
[0020] Each of the inlet 102, the main body 106, and the end portion 114
typically have non-circular and/or irregular cross-sectional shapes, although
circular or other regular shapes can be provided. Moreover due to its helical
geometry, the transition scroll 14 can be considered to have an inner section
140
and an outer section 142.
[0021] As discussed above, in many applications, cooling of the transition
scroll
14 is beneficial to prevent issues resulting from the high temperatures of the
exhaust gas of the combustor 12 (FIG. 1). The combustion gases directly
impinge
some of the hot or inner surfaces of the transition scroll 14, and are
redirected into
the turbine 22 (FIG. 1). The irregular cross-sections and helical shape of the
transition scroll 14 can additionally complicate some cooling schemes,
particularly attempts at louver and impingement cooling techniques.
[0022] In one exemplary embodiment, effusion cooling holes 150 are
provided in the transition scroll 14. The effusion cooling holes 150 are
generally
6

- - -- -CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
relatively small, closely spaced holes that permit compressed air from the
cold
side to pass through the respective wall of the transition scroll 14 for
supplying a
layer of cooling air to the hot side. In particular, the cooling air serves to
buffer
the hot side from the exhaust gases, as well as to convectively cool the
respective
wall of the transition scroll 14 as the air passes through, while having a
minimized
impact on the primary flow patterns.
[0023] Unlike the prior art cooling systems and methods that require heat
shields, impingement, and/or louvers, the effusion cooling holes 150 may
simplify
cooling in most embodiments in that no additional components need be attached
to the transition scroll 14. Such components may be provided in addition,
however, in embodiments where more cooling is desired. The durability of the
transition scroll 14 may be extended by a reduction in temperature gradients
along
the transition scroll 14, and additionally, manufacturing costs may be
reduced.
[0024] As a general matter, the effusion cooling holes 150 can be patterned to
further improve cooling. The effusion cooling holes 150 are typically
concentrated immediately downstream of the combustor exit where the
combustion gases are hottest. Moreover, the density of the effusion cooling
holes
150 may vary with application and may depend on factors, including the
dimensions of the transition scroll 14, the material of manufacture of the
transition
scroll 14, the velocity of the cooling flow, and the local temperature and
velocity
of the combustion gases. For some applications, the effusion cooling holes 150
may be uniformly spaced. Alternatively, the effusion cooling holes 150 may be
unevenly spaced to provide more cooling flow to potential "hot spots"
resulting
from the geometry of the transition scroll 14 and temperature characteristics
of the
combustion gases.
[0025] In the depicted embodiment, the inlet 102 has generally uniform
effusion
cooling holes 150 with a density of, for example, 20-30 holes per square inch.
At
least a portion of the top main body wall 108 has uniform effusion cooling
holes
7

- - --- - - - ---- .- - -CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
150 with a density of, for example, 10-20 holes per square inch. At least a
portion
of the inner main body wall 112 has uniform effusion cooling holes 150 with a
density of, for example, 20-30 holes per square inch; and at least a portion
of the
bottom main body wall 110 has uniform effusion cooling holes 150 with a
density
of, for example, 30-50 holes per square inch. In various embodiments, the
effusion cooling holes 150 on each of the components can be increased or
decreased as desired. For example, the effusion cooling holes can be 5 holes
per
square inch, or lower, or 100 holes per square inch, or higher. Generally, the
density of the effusion cooling holes is optimized to produce a constant
surface
temperature on the inlet 102 and body walls 108, 110, and 112.
[0026] In one embodiment, the density of the effusion cooling holes 150 of the
inlet 102 is greater than the density of the effusion cooling holes 150 of the
main
body 106. Moreover, additional effusion cooling holes 150 can be provided in
particular areas, such as on the inlet 102, top main body wall 108, and/or
bottom
main body wall 110 where the top and bottom main body walls 108, 110 meet the
inlet 102, such as on the outer section 142, as best shown in FIG. 3. The
effusion
cooling holes 150 extend along the transition scroll 14 as necessary to
provide
cooling. The depicted and disclosed effusion cooling hole patterns and
densities
are merely exemplary in nature, and such parameters vary based on application,
conditions, and desired level of cooling. For example, in some embodiments,
the
effusion cooling holes 150 extend along the length of the transition scroll
14,
including the end portion 114. The particular placement of effusion cooling
holes
150 can be assisted by computational fluid dynamics (CFD) analysis.
[0027] The effusion cooling holes 150 are generally 0.01 to 0.04 inches in
diameter, although the diameter may vary with application and may depend on
factors such as the dimensions of the transition scroll 14, the temperature of
the
combustion gases, and the velocity of the cooling flow. Individual hole shape
is
generally cylindrical or oval, with minor deviations due to manufacturing
method
i.e. edge rounding, tapers, out-of-round or oblong, etc. Other embodiments
could
8

- - ----- - - - ----- = - - CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
use holes with shapes other than circular or oval. The effusion cooling holes
150
are typically provided at acute angles, such as 20 , to the surface of the
transition
scroll 14. The effusion cooling holes 150 can be oriented along a flow
direction,
transverse to the flow direction, in between, or a combination of the three.
In one
embodiment, the angles of the effusion cooling holes 150 are varied adjacent
to
the manufacturing seams (e.g., seam 144 of FIG. 2 between the top main body
wall 108 and the inner main body wall 112) such that individual effusion
cooling
holes 150 do not traverse the seams, thereby enabling effusion hole drilling
prior
to transition scroll final assembly.
[0028] The transition scroll 14 may be constructed of any material suitable
for
high temperature combustible systems. Typically, the transition scroll 14 has
a
single wall construction, although other configurations such as double wall
constructions are also possible. Thin sheet metal capable of withstanding high
temperatures may be used to fabricate the transition scroll 14 through a
forming
process and machined rings (not shown) may be welded to the sheet metal to
form
specified interface characteristics and for structural reinforcement. Examples
of
suitable materials are nickel-based alloys, such as Inconel, Haynes 230 or
Hastelloy X.
[0029] The effusion cooling holes 150 may be formed by drilling techniques
such as electrical-discharge machining (EDM), stationary percussion laser
machining and percussion on-the-fly laser drilling or with complex casting
techniques.
[0030] Although the transition scroll 14 is configured for a single can
combustor
12, as illustrated herein, aspects of the present invention are also
applicable to
other types of combustors, such as multi-can and can-annular arrangements.
Engine assemblies of the present invention can be utilized in gas turbine
applications such as aircraft propulsion, land-based vehicle propulsion,
marine
based propulsion, auxiliary power units and power generation.
9

. ... .. . . ... ... . CA 02643956 2008-11-17
ATTORNEY DOCKET NO. H0016145
[00311 While at least one exemplary embodiment has been presented in the
foregoing detailed description of the invention, it should be appreciated that
a vast
number of variations exist. It should also be appreciated that the exemplary
embodiment or exemplary embodiments are only examples, and are not intended
to limit the scope, applicability, or configuration of the invention in any
way.
Rather, the foregoing detailed description will provide those skilled in the
art with
a convenient road map for implementing an exemplary embodiment of the
invention. It being understood that various changes may be made in the
function
and arrangement of elements described in an exemplary embodiment without
departing from the scope of the invention as set forth in the appended claims.

Dessin représentatif
Une figure unique qui représente un dessin illustrant l'invention.
États administratifs

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Historique d'événement

Description Date
Le délai pour l'annulation est expiré 2013-11-19
Demande non rétablie avant l'échéance 2013-11-19
Inactive : Abandon.-RE+surtaxe impayées-Corr envoyée 2013-11-18
Réputée abandonnée - omission de répondre à un avis sur les taxes pour le maintien en état 2012-11-19
Demande publiée (accessible au public) 2009-07-18
Inactive : Page couverture publiée 2009-07-17
Inactive : CIB en 1re position 2009-07-16
Inactive : CIB attribuée 2009-07-16
Inactive : CIB attribuée 2009-07-16
Inactive : CIB attribuée 2009-07-16
Exigences de dépôt - jugé conforme 2008-12-16
Inactive : Certificat de dépôt - Sans RE (Anglais) 2008-12-16
Demande reçue - nationale ordinaire 2008-12-12

Historique d'abandonnement

Date d'abandonnement Raison Date de rétablissement
2012-11-19

Taxes périodiques

Le dernier paiement a été reçu le 2011-10-31

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Historique des taxes

Type de taxes Anniversaire Échéance Date payée
Taxe pour le dépôt - générale 2008-11-17
TM (demande, 2e anniv.) - générale 02 2010-11-17 2010-10-21
TM (demande, 3e anniv.) - générale 03 2011-11-17 2011-10-31
Titulaires au dossier

Les titulaires actuels et antérieures au dossier sont affichés en ordre alphabétique.

Titulaires actuels au dossier
HONEYWELL INTERNATIONAL INC.
Titulaires antérieures au dossier
DAVID G. WALHOOD
GREGORY O. WOODCOCK
IAN L. CRITCHLEY
JURGEN C. SCHUMACHER
STONY W. KUJALA
Les propriétaires antérieurs qui ne figurent pas dans la liste des « Propriétaires au dossier » apparaîtront dans d'autres documents au dossier.
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Description du
Document 
Date
(aaaa-mm-jj) 
Nombre de pages   Taille de l'image (Ko) 
Description 2008-11-17 10 427
Abrégé 2008-11-17 1 18
Dessins 2008-11-17 3 79
Revendications 2008-11-17 4 115
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Rappel de taxe de maintien due 2010-07-20 1 114
Courtoisie - Lettre d'abandon (taxe de maintien en état) 2013-01-14 1 171
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Courtoisie - Lettre d'abandon (requête d'examen) 2014-01-13 1 165